• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The invention relates to a turbine blade having a platform cooling device for a platform (110) of the turbine blade, comprising: a platform slot formed in at least one of a pressure side slot side wall and a suction side slot side wall of the turbine blade; a releasably deployed baffle (130) that divides the platform slot into two radially stacked plenum chambers, a first plenum chamber (139) located radially further inward of a second plenum chamber (140); high pressure connection means (148) connecting said first plenum chamber (139) to a high pressure coolant portion of a cooling passage formed inside said turbine blade; low pressure connecting means (149) connecting the second plenum chamber (140) to a low pressure coolant portion of the cooling passage.
    公开号:CH703873B1
    申请号:CH01591/11
    申请日:2011-09-27
    公开日:2016-06-15
    发明作者:Wesley Harris John Jr；Edmond Ellis Scott；Fu Xiaoyong；Lional Scott Adrian
    申请人:Gen Electric；
    IPC主号:
    专利说明:

    Background to the invention
    The present invention relates to a turbine blade with a platform cooling device and a method for their preparation.
    A gas turbine usually includes a compressor, a combustion chamber and a turbine. The compressor and turbine generally include rows of airfoils or vanes stacked axially in stages. Each stage usually includes a series of circumferentially spaced stator blades that are stationary and a set of circumferentially spaced blades that rotate about a central axis or on a shaft. In operation, the blades in the compressor rotate on the shaft to compress airflow. The compressed air is then used within the combustion chamber to burn a supplied fuel. The resulting flow of hot gases from the combustion process is expanded as it passes through the turbine, causing the blades to rotate about the shaft to which they are attached. In this way, energy contained in the fuel is converted into the mechanical energy of the rotating shaft, which is then e.g. can be used to rotate the coils of a generator to generate electricity.
    [0003] Referring to FIGS. 1 and 2, turbine blades 100 generally include a airfoil-shaped portion or airfoil 102 and a root portion or root 104. The airfoil 102 may be described as having a convex suction surface 105 and a concave pressure surface 106. The airfoil 102 may also be described as having a leading edge 107 that is the leading edge and a trailing edge 108 that is the trailing edge. The foot 104 may be described as having a structure (which, as illustrated, typically includes a dovetail 109) for securing the blade 100 to the rotor shaft, a platform 110 from which the airfoil 102 extends, and a stem 112 having the structure between the dovetail 109 and the platform 110.
    As illustrated, the platform 110 may be substantially planar. (It should be noted that "as-is" as used herein means approximately or substantially the shape of a plane. "For example, one skilled in the art will recognize that platforms may be configured to have an outer surface is slightly curved or convex, the curvature with respect to the state of installation of the turbine blade in a turbine corresponds to the circumference of the turbine at the radial location of the blades As used herein, this type of platform shape is considered planar because the radius of curvature is large enough to be smooth In particular, platform 110 may have a planar top surface 113 which, as illustrated in FIG. 1, may include an axially and circumferentially extending flat surface. As illustrated in FIG. 2, the platform 110 may include a flat bottom 114 which may also include an axially and circumferentially extending flat surface. The top 113 and the bottom 114 of the platform 114 may be formed to be substantially parallel to each other. As illustrated, it is recognized that the platform 110 typically has a thin radial profile, that is, there is a relatively small radial distance between the top 113 and bottom 114 of the platform 110.
    In general, the platform 110 is used on turbine blades 100 to form an inner flow path boundary of the hot gas path region of the gas turbine engine. The platform 110 further provides structural support for the airfoil 102. In operation, the rotational speed of the turbine causes a mechanical stress that creates highly stressed regions along the platform 110 which, when coupled to high temperatures, eventually cause the formation of operational defects such as For example, oxidation, creep, cracking at low-frequency fatigue load and others cause. Of course, these defects negatively affect the useful life of the blade 100. It will be appreciated that these harsh operating conditions, i. exposure to extreme temperatures of the hot gas path and the mechanical stress associated with the blades result in significant challenges in designing durable, durable blade platforms 110 that both function well and are inexpensive to manufacture.
    One common approach to making the platform region 110 more durable is to cool it with a flow of compressed air or other coolant during operation, with many of these types of platform designs being known. However, one of ordinary skill in the art will recognize that platform region 110 offers certain design challenges that make cooling in this manner difficult. In essence, this is due to the unfavorable geometry of this region in that the platform 110, as described, is a peripheral component that is remote from the central core of the blade and is usually designed to be structurally robust, but low has radial thickness.
    To circulate a coolant, blades 100 typically include one or more hollow cooling channels 116 (see Figures 3, 4, and 5) extending at least radially through the core of the blade 100, including through the root 104 and the airfoil 102, extend. As described in more detail below, such cooling channels 116 may be formed to increase heat exchange with a serpentine path that winds through the central portions of the blade 100, although other configurations are possible. In operation, coolant may enter the central cooling channels via one or more inlets 117 formed in the inboard portion of the foot 104. The coolant may flow through the blade 100 and exit through outlets (not shown) formed on the airfoil and / or over one or more outlets (not shown) formed in the base 104. The coolant may be pressurized and may be e.g. Compressed air, mixed with water compressed air, steam and the like. In many cases, the refrigerant is compressed air that is discharged from the compressor of the machine, although other sources are possible. As described in more detail below, these cooling passages typically include a high pressure coolant area and a low pressure coolant area. The high-pressure refrigerant area usually corresponds to an upstream portion of the cooling passage having a higher refrigerant pressure while the low-pressure refrigerant area corresponds to a downstream portion having a relatively lower refrigerant pressure.
    In many cases, the coolant may be introduced from the cooling channels 116 into a cavity 119 formed between the shafts 112 and the platforms 110 of adjacent blades 100. From there, the coolant may be used to cool the platform region 110 of the blade, a conventional design of which is shown in FIG. This type of construction typically draws air from one of the cooling channels 116 and uses the air to pressurize the cavity 119 formed between the shafts 112 / platforms 110. Once pressurized, this cavity 119 then delivers the coolant to cooling channels that extend through the platforms 110. After flowing through the platform 110, the cooling air may exit the cavity through film cooling holes formed in the top surface 113 of the platform 110.
    However, it will be appreciated that this type of conventional construction has several disadvantages. First, the refrigeration cycle is not self-contained in a single component because the refrigeration cycle is not formed until two adjacent blades 100 are assembled. This contributes to a high degree of difficulty and a high level of complexity during installation and flow tests before installation. A second disadvantage is that the entirety of the cavity 119 formed between adjacent blades 100 depends on how well the periphery of the cavity 119 is sealed. Insufficient sealing may result in insufficient platform cooling and / or wasted cooling air. A third disadvantage is the inherent danger that hot gas path gases may be sucked into the cavity 119 or the platform 110 itself. This can occur if the cavity 119 is not maintained at a sufficiently high pressure during operation. If the pressure of the cavity 119 falls below the pressure within the hot gas path, hot gases are drawn into the shaft cavity 119 or the platform 110 itself, which usually damages these components since they are not designed to be subjected to stress under the hot gas path conditions.
    Figures 4 and 5 illustrate another type of conventional platform cooling design. In this case, the refrigeration cycle is contained within the blade 100 and does not include the stem cavity 119, as shown. Cooling air is withdrawn from one of the cooling channels 116 passing through the core of the blade 110 and directed backward by cooling channels 120 formed within the platform 110 (i.e., "platform cooling channels 120"). As illustrated by the various arrows, the cooling air flows through the platform cooling channels 120 and exits through outlets in the rear edge 121 of the platform 110 or outlets disposed along the suction side edge 122. (It should be noted that in describing or referring to the edges or side walls of the rectangular platform 110, each based on its location with respect to the suction surface 105 and pressure surface 106 of the airfoil 102 and / or the forward and rearward directions As such, one skilled in the art will understand that the platform may include a trailing edge 121, a suction side edge 122, a leading edge 124 and a pressure side edge 126 as shown in Figs 3 and 4. In addition, suction side edge 122 and pressure side edge 126 are commonly referred to as "slot sidewalls," and the narrow cavity formed therebetween when adjacent blades 100 are installed may be referred to as a "slot sidewall cavity."
    It will be appreciated that the conventional structures of FIGS. 4 and 5 have an advantage over the construction of FIG. 3 in that they are unaffected by variations in assembly or installation conditions. However, conventional designs of this type have several limitations or disadvantages. First, as illustrated, only a single circuit is provided on each side of the airfoil 102, and thus there is the disadvantage that there is limited control or control of the amount of cooling air used at different locations in the platform 110. Second, conventional designs of this type have a coverage area that is substantially limited. While the serpentine path of FIG. 5 is an improvement over the coverage of FIG. 4, there are still dead areas within the platform 110 that remain uncooled. Third, the manufacturing cost to obtain a better coverage area with complex shaped platform cooling channels increases significantly, especially if the cooling channels have molds that require a casting process for their manufacture. Fourth, these conventional designs typically emit the coolant into the hot gas path after it has been used and before the coolant is completely depleted, adversely affecting the efficiency of the engine. Fifth, conventional designs of this type generally have little flexibility. That is, the channels 120 are created as an integral part of the platform 110 and provide little or no opportunity to change their function or configuration as operating conditions vary. Moreover, these types of conventional designs are difficult to repair or overhaul.
    As a result, conventional platform cooling designs are lacking in one or more important areas. It is therefore an object of the present invention to provide a turbine blade with an improved platform cooling device that effectively and efficiently cools the platform region of the turbine blade while also being inexpensive to manufacture, flexible to use, and durable.
    Brief description of the invention
    This object is achieved by a turbine blade with a platform cooling arrangement according to claim 1.
    The invention further relates to a method for producing such a turbine blade with a platform cooling arrangement.
    These and other features of the present invention will become more apparent upon a review of the following detailed description of the preferred embodiments taken in conjunction with the drawings.
    Brief description of the drawings
    These and other features of the invention will be more fully understood and appreciated on reading the following detailed description of exemplary embodiments of the invention in conjunction with the accompanying drawings in which:<Tb> FIG. 1 <SEP> is a perspective view of an exemplary turbine blade in which embodiments of the present invention may be used;<Tb> FIG. 2 <SEP> is a bottom view of a turbine blade in which embodiments of the present invention may be used;<Tb> FIG. 3 <SEP> is a sectional view of adjacent turbine blades with a cooling system according to a conventional construction;<Tb> FIG. FIG. 4 is a plan view of a turbine blade having a platform with internal cooling channels according to a conventional construction; FIG.<Tb> FIG. 5 is a plan view of a turbine blade having a platform with internal cooling channels, according to an alternative conventional design;<Tb> FIG. FIG. 6 is a disassembled perspective view of a turbine blade and platform impactor according to an exemplary embodiment of the present invention; FIG.<Tb> FIG. FIG. 7 is a partially cutaway plan view of the turbine blade and platform baffle according to an exemplary embodiment of the present invention; FIG.<Tb> FIG. FIG. 8 is a partially cutaway side view of the turbine blade and platform baffle according to an exemplary embodiment of the present invention; FIG.<Tb> FIG. FIG. 9 is a partially cutaway side view of the turbine blade and platform baffle according to an exemplary embodiment of the present invention; FIG.<Tb> FIG. 10 is a perspective view of a bale insert according to an exemplary embodiment of the present invention;<Tb> FIG. 11 is a perspective view of a bale insert according to a modified exemplary embodiment of the present invention; and<Tb> FIG. 12 is a flowchart of a method according to an exemplary embodiment of the present invention.
    Detailed description of the invention
    It will be understood that turbine blades cooled via the internal circulation of a coolant will usually include an internal cooling channel 116 which extends radially outwardly from the foot through the platform region and into the airfoil as above with respect to various conventional refrigeration designs. It will be understood that certain embodiments of the present invention may be used in conjunction with conventional coolant channels to enhance or facilitate efficient active platform cooling, so that the present invention will be described in connection with a common design: an inner cooling channel 116 having a winding or serpentine configuration. As shown in FIGS. 7, 10, and 11, the serpentine path is usually configured to allow one-way flow of coolant in one direction and includes features that facilitate heat exchange between the coolant and the surrounding blade 100. In operation, a pressurized refrigerant, which is usually compressed air from the compressor (although other types of refrigerant, such as steam, may also be used in the embodiments of the present invention), passes to the inner cooling channel 116 through one through the foot 104 created connection delivered. The pressure drives the coolant through the inner cooling passage 116, and the refrigerant conducts heat from the surrounding walls by convection.
    It is to be understood that the refrigerant, as it flows through the cooling passage 116, loses pressure, the coolant in the upstream portions of the inner cooling passage 116 having a higher pressure than the refrigerant in downstream portions. As discussed in more detail below, this pressure differential may be used to drive the coolant over or through cooling channels formed in the platform. It is understood that the present invention can be used in blades 100 having internal cooling channels of different configurations and not limited to internal cooling channels having a serpentine shape. Accordingly, the term "inner cooling channel" or "cooling channel" as used herein is intended to mean having any passageway or hollow channel through which coolant can be flowed in the blade. As provided herein, the inner cooling passage 116 according to the present invention extends to at least the approximate radial height of the platform 110 and may include at least one relatively higher coolant pressure region (hereinafter referred to as a "high pressure region") in some cases may be an upstream portion within a serpentine channel) and at least one region of relatively lower coolant pressure (hereinafter referred to as a "low pressure region") and a downstream region within a high pressure region serpentine channel).
    [131] In general, the various constructions of the conventional internal cooling channels 116 are effective in providing active cooling for particular areas within the blade 100. However, as one skilled in the art will recognize, the platform region proves to be more challenging. This stems, at least in part, from the unfavorable geometry of the platform - i. its small radial height and the manner in which it protrudes from the core or main body of the blade 100 - ago. However, given their stresses due to the extreme temperatures of the hot gas path and the high mechanical stress, the cooling requirements of the platform are considerable. As described above, conventional platform cooling designs are ineffective because they do not address the region's specific challenges of being inefficient and / or costly to produce when using the coolant.
    Figs. 6 to 12 show various views of exemplary embodiments of the present invention. Referring to FIG. 6, a perspective view of a turbine blade 100 and a baffle insert 130 according to one embodiment of the present invention is shown. As illustrated, the present invention generally includes a releasable baffle 130 installed in a turbine blade 100. In particular, the platform 110 of the bucket 100 may include a platform slot 134 configured to fit the bale insert 130 therein. In a preferred embodiment, as illustrated, the platform slot may be positioned in the pressure-side edge or slot sidewall 126, although other locations along the other edges of the platform 110, such as the suction-side slot sidewall 122, are also possible. The platform slot 134 may have a rectangular shaped mouth opening and may be described as including an outer surface or ceiling 135 and an inner surface or floor 136. As illustrated, the mouth opening may be configured to be relatively thin in the radial direction and relatively wide in the axial direction. It is understood that the platform slot 134 extends circumferentially from the mouth opening into the platform 110, thereby forming a cavity therein.
    The platform bounce insert 130 may have a flat, thin disk-like shape and may be configured to fit within the platform slot 134 and generally have a similar profile (i.e., from the viewpoint of Figure 7) as the platform slot 134. The baffle 130 may include a plurality of baffles 132, the function of which is explained in more detail below. The baffle 130 may further include a spacer 138 extending from an outer surface. In addition, a closure 137 may be included which encloses the mouth opening of the platform slot 134. The closure 137 has, as illustrated, a flat, rectangular outer surface which, when the bale insert 130 is properly installed in the platform slot 134, substantially covers, obstructs or seals the mouth opening of the platform slot 134. In some preferred embodiments, the closure 137, as described in more detail below, prevents the coolant from exiting the blade 100 through the mouth opening of the platform slot 134.
    The shape of the platform slot 134 may vary. In a preferred embodiment, as more clearly illustrated in FIG. 7, the platform slot 134 may extend circumferentially from the pressure side slot side wall or edge 126. It will be appreciated that in this preferred embodiment, the platform slot 134 narrows in its course from the pressure-side slot sidewall 126 toward the center of the platform 110. The constriction may substantially correspond to the curved profile formed at the junction between the airfoil pressure surface 106 and the platform 110. As such, the platform slot 134 may have a curved back wall or inner wall in profile (i.e., in the form of the angle of view of Figure 7) that is closely related to the curved profile of the airfoil thrust surface 106. It should be apparent to those skilled in the art that other configurations of the platform slot 134 may also be used. However, it will be appreciated that the preferred embodiments of FIGS. 6-11 effectively cope with the cooling requirements for a large coverage area containing some of the more difficult to cool areas within platform 110. Those skilled in the art will understand that further performance benefits and efficiencies are possible.
    The baffle insert 130 and the platform slot 134 may be configured such that in the assembled state, two radially stacked plenum chambers 139, 140 are formed within the platform slot 134. Specifically, as more clearly illustrated in FIG. 8, the baffle 130 substantially bisects the platform slot 134 such that a first plenum 139 (which may also be referred to as an "inner plenum" or "pre-impact plenum") extends along the underside of the bale insert 130 is formed, and a second plenum 140 (which may also be referred to as an "outer plenum" or "rebound plenum") is formed along the top of the bale insert 130.
    As most clearly illustrated in FIGS. 7 and 8, two connectors, a high pressure connector 148 and a low pressure connector 149, may be provided to connect the inner cooling channel 116 to the platform slot 134 in a desired manner. While not specifically indicated, it should be understood that the following description assumes that the upstream portions of the inner cooling channel 116 are closer to the leading edge 107 of the blade 100 and that the downstream portions of the inner cooling channel 116 are closer to the trailing edge 108 of the turbine blade 100 toward. Although this configuration is commonly used, it is not necessary to practice the present invention because the arrangement of the platform slot 134 and connectors 148, 149 can be adjusted to suit other configurations. As illustrated in FIG. 8, in a preferred embodiment, the high pressure connector 148 is connected to the platform slot 134 at a more inward radial position than the low pressure connector 149. In this way, the high pressure connector 148 may be configured to be connected to the outer plenum 140, while the low pressure connector 149 may be configured to connect to the inner plenum 139.
    Fig. 9 illustrates another embodiment of the present invention. In Fig. 9, the platform slot 134 is configured with a notch 151 that can support the bale insert 130 at its peripheral edge. As illustrated, a spacer 138 may also be included for support along the central portions of the insert 130, or in other embodiments, the spacer 138 may be entirely removed. It will be appreciated that the notch 151 may enhance the seal around the insert 130 such that more of the coolant is passed through the impingement openings. It will be appreciated that the notch will be configured such that the centrifugal load will push the insert 130 against the shoulder 151 during operation of the machine and that the notch 151 will be configured so that, when this occurs, the insert 151 at one desired position is held.
    In operation, coolant may enter the inner cooling passage 116 at a position proximate the leading edge 107 of the airfoil 102 and alternately flow radially outwardly / inwardly through the inner cooling passage 116 while winding in a rearward direction , As illustrated, the high pressure connector 148 may be configured such that an upstream (and higher pressure) portion of the inner cooling passage 116 communicates with a predetermined portion of the platform slot 134 that forms the inner plenum 139 as described. Further, the low pressure connector 149 may be configured such that a downstream portion of the inner cooling channel communicates with a predetermined portion of the platform slot 134 which, as described, forms the outer plenum chamber 140.
    Although in some embodiments the insert 130 may be rigidly secured to a preferred location, in a preferred embodiment, the baffle 130 may remain free-floating after mounting in the platform slot 134. That is, the bale insert 130 is positioned in the platform slot 134 and is not attached to any of the walls of the platform slot 134. The closure 137 can then be used to sealingly close the mouth opening of the platform slot 134. This allows the insert 130 to be retained within the platform slot 134 while still allowing some movement. In a preferred embodiment, the profile of the platform insert 130 closely matches the profile of the platform slot 134, the profile of the platform insert 130 being only slightly smaller. In this case, it will be understood that once the platform insert 130 is placed in the platform slot 134, the insert 130 will have a slight clearance between its outer periphery and the surrounding walls of the slot 134 and on one side of the closure 137. The insert 130 is thus substantially prevented from significant movement in the axial and circumferential directions. In some embodiments, as illustrated, the radial height of the baffle 130 is significantly less than the radial height of the platform slot 134. This configuration may allow the insert 130 some limited movement in the radial direction.
    The closure 137 may be sealed by conventional methods. This may be done to support the insert 130 in the slot 134 and also to prevent or avoid leakage through the slot sidewall and / or coolant leakage into the hot gas path at that location. It will be appreciated that preventing leakage current through the pressure side slot sidewall 126 means that substantially all of the coolant flowing through the platform slot 134 is directed back into the inner cooling channel 116, where it is also used to cool other portions of the blade 100 or can be used in any other way. In an alternative embodiment, the closure 137 may include a limited number of baffles (not shown) that direct an impinged coolant flow within the slot sidewall cavity formed between two installed blades.
    As most clearly illustrated in Figs. 10 and 11, the baffle 130 generally includes a plurality of baffles 132 to achieve cooling of the platform 110. The baffles 132 of the insert 130 may be arranged in multiple rows, although other configurations possible are. The bale insert 130 may include a curved edge 154 and a straight edge 155, as illustrated. In one embodiment of the present invention, the curved edge 154 may approximately match in shape with the curved profile of the airfoil 102. The rows of baffles 132 may be oriented substantially perpendicular or oblique to the straight edge 155 of the baffle 130. However, the baffles 132 may be arranged in any other configuration (e.g., staggered) without departing from the scope of the present application.
    It is understood that the baffles 132 may be configured to direct impacted high velocity coolant streams against the ceiling 135 of the platform slot 134. Since the ceiling 135 is opposed to the platform top 113 over a relatively narrow portion of the platform 134, cooling the ceiling 135 in this manner provides an effective way of cooling the platform top 113 which, being exposed to the hot gas path during operation, is in need Area forms. As stated, these coolant streams are driven by the differential pressure existing between the locations where the high pressure connector 148 and the low pressure connector 149 are connected to the inner cooling channel 160. It is understood that such impingement cooling can enhance the cooling effect of the coolant flowing through the platform slot 134. In an embodiment of the present application, the impact openings 132 may have a substantially cylindrical shape. However, other shapes of the baffles 132 may be possible, such as, but not limited to, cubic, prismatic, and the like. Further, the baffles 132 may be aligned substantially perpendicular to the surface of the baffle 130. The baffles 132 may also be oriented obliquely with respect to the surface of the baffle 130 without departing from the scope of the subject application.
    As stated, in one embodiment of the present invention, the baffle 130 may include a spacer 138. It will be appreciated that during operation, centrifugal loads will push the insert 130 against the ceiling 135 of the platform slot 134. The spacers 138 may thus be used to establish the radial height of the first and second plenums 139, 140 during operation of the machine. In a preferred embodiment, as illustrated in FIG. 10, the spacer 138 may include a plurality of cylindrical protrusions. The protrusions may be the same height such that the height of the second plenum 140 across the platform slot 134 is relatively constant during operation. It is understood that the height of the second plenum chamber 140 (i.e., the height of the spacer 138) may be based on a distance at which the impingement cooling of the ceiling 135 has a desired heat transfer characteristic or is suitably maximized.
    In another embodiment of the present invention, as illustrated in FIG. 11, the spacer 138 may include a raised edge extending around the perimeter of the bale insert 130. In this case, the configuration of the spacer 138 is used to improve the separation or sealing between the first plenum chamber 139 and the second plenum chamber 140, as a centrifugal load during operation pushes the raised edge 138 against the slot ceiling 135. It will be understood that this reduces the amount of coolant flowing through this potential leakage path, which would reduce the amount of coolant flowing around the impingement ports 132, and thereby improve the cooling performance by driving more coolant through the intended path ,
    According to the present invention, the first plenum 139 includes at least one inlet or inlet channel (which may be referred to as a high pressure connector 148) in fluid communication with the high pressure area of the inner cooling channel 116. The second plenum 140 includes at least one outlet or outlet channel (which may be referred to as a low pressure connector 149) in fluid communication with the low pressure coolant portion of the inner cooling passage 116. In various embodiments of the present invention, the high pressure connector 148 and / or the low pressure connector 149 may be manufactured by one or more methods such as, but not limited to, machining, molding, and the like.
    During operation, the coolant flowing through the high-pressure coolant region of the inner cooling passage 116 enters the first plenum chamber 139 via the high-pressure connection device 148. Subsequently, the coolant flows through the impact openings 132 to the second plenum chamber 140 and substantially accomplishes the impingement cooling of the platform 110 by bouncing against the ceiling 135 of the platform slot 134. The coolant then exits the second plenum chamber 140 to the low-pressure coolant region of the inner cooling passage 116 via the low-pressure connection device 149. As explained, due to the aforementioned functional relationship between various components, the first plenum chamber 139 and the second plenum chamber 140 may also be referred to as an advance-plenum chamber and a rebound-plenum chamber, respectively.
    The present invention further includes a novel method of creating effective internal cooling channels within the platform region of the blade in a cost effective and efficient manner. As illustrated in FIG. 12, in an initial step 202, the platform slot 134 may be created in the pressure-side slot sidewall 126 of the platform 110. Due to the relatively uncomplicated shape of the platform slot 134, it can be inexpensively produced using conventional machining or simplified molding processes. Expensive casting processes used for more complex designs can be avoided.
    In step 204, after the platform slot 134 has been formed, the high pressure connector 148 and the low pressure connector 149 may be created with a conventional machining process. In particular, the connectors 148, 149 may be created at the access provided by the generated platform slot 134 with a conventional line-of-sight machining or drilling process.
    Separately, in a step 206, the platform bounce insert 130 may be manufactured in a desired manner, the size and shape of which are desirably related to the size of the platform slot 134, as discussed above.
    In step 208, the baffle 130 may then be installed in the platform slot 134. As noted, in one preferred embodiment, the baffle 130 may be positioned within the slot 134, but not secured to any of the walls of the slot 134, that is, the insert 130 may remain levitated.
    Finally, in step 210, the shutter 137 can be installed. This may be done by conventional methods and, as described, sealingly close the slot 134 so that the coolant flowing into the slot 134 from the inner cooling channels 116 of the blade 100 is returned.
    In operation, the cooling device according to the present invention may function as follows: A portion of the supplied coolant flowing through the inner cooling passage 116 enters the inner or pre-rebound plenum 139 through the high-pressure connection device 148. The coolant is impinged by the baffles 132 of the insert 130 and directed into the outer or rebound plenum 140 and toward the ceiling 145 of the slot 134 where the refrigerant dissipates heat from the platform 110 by convection. From the rebound plenum chamber 140, the coolant may be returned to the inner cooling passage 116 of the blade 100 via the low pressure connection means 149. In this way, the platform cooling device according to the present invention removes part of the coolant from the inner cooling channel 116, uses the coolant to remove heat from the platform 110, and then returns the coolant to the inner cooling channel 116 where it can continue to be used.
    It is understood that the present invention provides a mechanism by which the platform region of a blade of a combustion turbine can be actively cooled. As stated, this range is usually difficult to cool, and at the given mechanical stresses of this range, it represents a location which suffers greatly as firing temperatures are increased. Accordingly, this type of active platform cooling represents a substantial viable technology if higher firing temperatures, increased power output, and greater efficiency are desired.
    Further, it will be understood that the removable platform bounce insert 130 according to the present invention provides greater flexibility in reshaping, reconfiguring or retrofitting or tuning the cooling devices on existing blades. That is, the platform bounce insert 130 allows the cooling circuit passing through the platform 110 to be replaced in a cost effective and convenient manner if operating conditions change or greater cooling by the platform region is required. In addition, the replaceable structure is particularly helpful during the testing phase in that alternative designs can be more conveniently tested. The detachable insert also allows the simplified production of impingement cooling structures. While previously such complex geometries necessarily meant a costly casting process, the present invention teaches methods by which internal impingement cooling structures can be created by a combination of simple machine fabrication and / or simplified casting processes. Finally, the present invention teaches a method by which the platform 110 can be cooled using internal channels that do not vent directly from the platform 110 into the hot gas path itself. As stated, this "recycling" of the refrigerant generally increases the efficiency of its use, which increases the efficiency of the machine.
    Further, as described, insert 130 may remain levitated within platform slot 134, providing various performance benefits. First, the motion may have a damping effect that could be used to eliminate or reduce some of the unwanted vibration that occurs during engine operation. Further, it will be understood by those skilled in the art that the free-floating nature of the assembly would prevent heat-induced stress in the blade, thereby reducing platform stresses.
    [0044] The invention relates to a turbine blade having a platform cooling device for a platform 110 of the turbine blade, comprising: a platform slot formed in at least one of a pressure side slot side wall and a suction side slot side wall of the turbine blade; a releasably deployed baffle 130 that divides the platform slot into two radially stacked plenum chambers, with a first plenum 139 located radially further inward from a second plenum 140; a high pressure connection device 148 connecting the first plenum 139 to a high pressure refrigerant section of a cooling passage formed inside the turbine blade; a low pressure connector 149 connecting the second plenum chamber 140 to a low pressure coolant portion of the cooling passage.
    LIST OF REFERENCE NUMBERS
    [0045]<Tb> 100 <September> turbine blade<Tb> 102 <September> blade<Tb> 104 <September> foot<Tb> 105 <September> suction<Tb> 106 <September> print area<Tb> 107 <September> leading edge<Tb> 108 <September> trailing edge<Tb> 109 <September> Swallowtail<Tb> 110 <September> Platform<Tb> 112 <September> End<Tb> 113 <September> Platform top<Tb> 114 <September> Platform base<tb> 116 <SEP> Inner cooling channel<Tb> 117 <September> inlet<Tb> 119 <September> cavity<Tb> 120 <September> platform cooling channels<tb> 121 <SEP> back edge<tb> 122 <SEP> suction side edge or slot side wall<tb> 124 <SEP> leading edge<tb> 126 <SEP> Print-side edge or slit sidewall<Tb> 130 <September> Impact application<Tb> 132 <September> impingement holes<Tb> 134 <September> Platform slot<Tb> 135 <September> slot ceiling<Tb> 136 <September> slot base<Tb> 137 <September> closure<Tb> 138 <September> Spacers<tb> 139 <SEP> first plenum chamber (inner plenum chamber or pre-plunge chamber)<tb> 140 <SEP> second plenum chamber (outer plenum chamber or rebound plenum chamber)<Tb> 148 <September> high-pressure connector<Tb> 149 <September> low-pressure connector<Tb> 151 <September> notch<tb> 154 <SEP> curved edge<tb> 155 <SEP> straight edge
    权利要求:
    Claims (10)
    [1]
    A turbine blade (100) having a platform cooling device, the turbine blade (100) comprising:a platform (110) at a junction between an airfoil (102) and a foot (104),a cooling passage (116) formed in the interior of the turbine bucket (100) and relating to the installed state of the turbine bucket (100) in a turbine from a connection to a source of coolant at the foot (104) to at least the radial height of the platform (110) wherein, in operation, the inner cooling passage (116) has a high pressure coolant area and a low pressure coolant area,wherein the platform (110) has a radially outwardly facing top surface (113) circumferentially in relation to the installed state of the turbine blade (100) in a turbine along a pressure side coincident with a pressure side (106) of the airfoil (102) from the airfoil (102) to a pressure-side slit sidewall (126) and along a suction side coincident with a suction side (105) of the airfoil (102) has a radially outwardly facing top surface (113) extending circumferentially from the airfoil (102) to a suction-side slotted sidewall (122),wherein the platform cooling device comprises:a platform slot (134) formed in at least one of the pressure-side slot sidewall (126) and the suction-side slot sidewall (122);a baffle insert (130) releasably inserted into the platform slot (134) dividing the platform slot (134) into two plenum chambers radially stacked with respect to the installed state of the turbine blade (100), wherein a first one of the turbine blade (100) is installed in a turbine Plenum chamber (139) located radially inward of a second plenum chamber (140);high pressure connection means (148) connecting the first plenum chamber (139) to the high pressure coolant portion of the cooling passage (116); anda low pressure connection means (149) connecting the second plenum chamber (140) to the low pressure coolant portion of the cooling passage (116);wherein the baffle insert (130) has a plurality of impact openings (132).
    [2]
    2. A turbine blade (100) according to claim 1, wherein:the top surface (113) of the platform (110) is planar and parallel to a flat underside (114) of the platform (110);the platform slot (134) has a planar ceiling (135) located in an area adjacent the top surface (113) of the platform (110) with respect to the installed state of the turbine blade (100) in a turbine, and a planar floor (136) located in an area adjacent to the underside (114) of the platform (110); wherein the platform slot (134) is formed in the pressure-side slot sidewall (126);the baffle insert (130) has a disk-like plate structure having a planar radially outwardly facing outer surface and a planar radially inwardly facing inner surface with respect to the installed state of the turbine blade (100) in a turbine; andthe baffles (132) extend from the outer surface to the inner surface through the baffle (130) and are configured to impinge a coolant flow and direct the bounced coolant flow against the ceiling (135) of the platform slot (134).
    [3]
    The turbine blade (100) of claim 2, wherein the location at which the high pressure connector (148) is connected to the platform slot (134) has an axially upstream position relative to the installed state of the turbine blade (100) with respect to Location where the low pressure connector (149) is connected to the platform slot (134); andwherein the platform slot (134) is configured such that from a mouth opening along the pressure side slot side wall (126), the axial extent of the platform (134) relative to the installed state of the turbine blade (100) in a turbine decreases while the platform slot (134) extends circumferentially into the platform (110) with respect to the installed state of the turbine blade (100).
    [4]
    4. A turbine blade (100) according to claim 2, wherein in profile an inner wall of the platform slot (134) is curved, the curved profile with respect to the shape and position of the curved profile of the pressure side of the airfoil (102) where the pressure side of the airfoil ( 102) and the platform (110) meet, corresponds; andwherein the inner wall has a notch (151), wherein the notch (151) is configured such that the peripheral edge of the baffle insert (130) is fit to fit therein.
    [5]
    The turbine blade (100) of claim 4, wherein the notch (151) is configured such that when the baffle insert (130) is biased toward the ceiling (135) of the platform slot (134) by the centrifugal operating load, the notch (151) engages the peripheral edge of the baffle (130) and thereby holds the baffle (130) a predetermined distance from the top (135) of the platform slot (134);further comprising a closure (137) configured to substantially sealingly close the mouth opening of the platform slot (134) such that in operation substantially all of the coolant flowing through the platform slot (134) is directed to the inner cooling channel (134). 116) is returned.
    [6]
    6. turbine blade (100) according to claim 2, wherein on the outer surface of the baffle insert (130) comprises a spacer (138);wherein the spacer (138) has one or more rigid protrusions protruding from the surface of the outer surface by a predetermined length; andwherein in the biased by the centrifugal operating load towards the ceiling (135) of the platform slot (134) state of the spacer (138) is configured to the outer surface of the baffle (130) at a predetermined distance to the ceiling (135) of the platform slot (134).
    [7]
    The turbine blade (100) of claim 2, wherein the baffle (130) is disposed within the platform slot (134) with radial play.
    [8]
    8. A method of manufacturing a turbine blade (100) with a platform cooling device according to claim 1, said method comprising the steps of:Creating the platform slot (134) in the platform (110), the platform slot (134) extending circumferentially from a mouth opening formed in the pressure-side slot sidewall (126);machining the high pressure connector (148) from the interior of the generated platform slot connecting a first predetermined location within the platform slot (134) to the high pressure coolant portion of the cooling channel (116);machining the low pressure connector (149) from the interior of the created platform slot connecting a second predetermined location within the platform slot (134) to the low pressure coolant portion of the cooling channel (116); andProducing the bale insert (130) containing the plurality of baffle openings (132) and having a predetermined configuration corresponding to the size of the platform slot (134); andInstalling the baffle (130) within the platform slot (134);wherein, when installed, the baffle (130) divides the platform slot into the first and second plenums radially stacked with respect to the installed state of the turbine blade (100).
    [9]
    9. The method of claim 8, wherein:the first predetermined location within the first plenum andthe second predetermined location is within the second plenum chamber;further comprising the steps:Placing the bale insert (130) in the platform slot (134) such that the baffle insert (130) is disposed therein with radial play; andInstalling a closure (137) over the mouth opening of the platform slot (134).
    [10]
    10. The method of claim 9, wherein:the baffle insert (130) has a disk-like plate structure having a planar radially outwardly facing outer surface and a planar radially inwardly facing inner surface with respect to the installed state of the turbine blade (100);the baffles (132) extend through the baffle (130) from the outer surface to the inner surface and are configured to impinge a coolant flow and direct the bumped coolant flow against a ceiling (135) of the platform slot (134);on the outer surface of the baffle insert (130) comprises a spacer (138), the spacer (138) having one or more rigid projections projecting from the surface of the outer surface by a predetermined length; andwhen the baffle (130) is biased toward the ceiling (135) of the platform slot (134) by the centrifugal operational load, the spacer (138) is configured to close the outer surface of the baffle (130) a predetermined distance from the ceiling (135) of the platform slot (134).
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    同族专利:
    公开号 | 公开日
    CH703873A2|2012-03-30|
    DE102011053873A1|2012-04-05|
    CN102444431A|2012-05-09|
    JP2012077749A|2012-04-19|
    CN102444431B|2015-11-25|
    US8684664B2|2014-04-01|
    JP5898902B2|2016-04-06|
    US20120082550A1|2012-04-05|
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    法律状态:
    2017-03-15| NV| New agent|Representative=s name: GENERAL ELECTRIC TECHNOLOGY GMBH GLOBAL PATENT, CH |
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    优先权:
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    US12/895,035|US8684664B2|2010-09-30|2010-09-30|Apparatus and methods for cooling platform regions of turbine rotor blades|
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