• 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:
    A turbine rotor blade is provided with a platform cooling device (130), the turbine rotor blade having a platform at a transition between an airfoil (102) and a foot (104) and a cooling channel (116) operatively having at least one high pressure coolant region and one low pressure coolant region wherein the platform has a platform underside (114). The platform cooling device (130) includes: a plate (132) having a top surface; a channel (133) formed on the top of the plate, the channel (133) having an upstream end (138) and a downstream end (139) and being open on the top of the plate such that the platform underside includes a channel cover (140) when the channel top (133) Plate (132) is attached to the platform (110); a high pressure port (148) connecting the upstream end (138) of the passage (133) to the high pressure coolant portion of the inner cooling passage (116); and a low pressure port (149) connecting the downstream end (139) of the duct (133) to the low pressure coolant portion of the inner cooling duct (116).
    公开号:CH703877B1
    申请号:CH01593/11
    申请日:2011-09-27
    公开日:2016-01-15
    发明作者:Scott Edmond Ellis；John Wesley Harris Jr；Adrian Lional Scott
    申请人:Gen Electric；
    IPC主号:
    专利说明:

    Background of the invention
    The present invention relates to a turbine rotor blade with a platform cooling device and a method for their preparation.
    A gas turbine plant typically includes a compressor, a combustor and a turbine. The compressor and the turbine generally have rows of blades or blades lined up axially in stages. Each stage typically includes a series of circumferentially spaced stator vanes that are stationary and a group of circumferentially spaced rotor vanes that rotate about a central axis or shaft. In operation, the rotor blades in the compressor are rotated about the shaft to compress an airflow. The compressed air is then used in the combustion chamber to burn a supplied fuel. The resulting stream of hot gases from the combustion process is expanded in the turbine, causing the rotor blades to rotate 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 energy is then applied e.g. for rotating the coils of a generator can be used to generate electricity.
    Referring to FIGS. 1 and 2, turbine rotor blades 100 generally include an airfoil portion or airfoil 102 and a foot portion or foot 104. The airfoil 102 may be described as having a convex suction surface 105 and a concave pressure surface 106. The airfoil 102 may be further 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 (typically including a dovetail 109, as shown) for securing the blade 100 to the rotor shaft, a platform 110 from which the airfoil 102 extends, and a stem 112, which includes the structure between the dovetail 109 and the platform 110.
    As shown, the platform 110 may be substantially planar. Specifically, the platform 110 may have a planar top surface 113 which, as shown in FIG. 1, may have an axially and circumferentially extending planar surface. As shown in FIG. 2, the platform 110 may include a flat bottom 114 which may also have an axially and circumferentially extending planar surface. The top 113 and bottom 114 of the platform 110 may be formed to be substantially parallel to each other. As shown, it is recognized that the platform 110 typically has a thin radial profile, that is, there is a relatively short radial distance between the top 113 and bottom 114 of the platform 110.
    Generally, the platform 110 on turbine rotor blades 100 is used to form the inner flow path boundary of the hot gas path portion of the gas turbine. The platform 110 further provides structural support for the airfoil 102. In operation, the rotational speed of the turbine exerts a mechanical load that creates high stress areas along the platform 110 which, in conjunction with high temperatures, ultimately results in the formation of operational defects, such as air. Oxidation, creep, fatigue failure at low load cycles and others cause. Of course, these defects adversely affect the useful life of the rotor blade 100. It will be appreciated that these harsh operating conditions, i. contact with extreme temperatures of the hot gas path as well as the mechanical loading associated with the rotating blades pose significant challenges in designing durable, durable rotor blade platforms 110 that function well as well as being inexpensive to manufacture.
    A common solution for making the platform portion 110 more durable is to cool it during operation with a stream of compressed air or other coolant, and a variety of these types of platform designs are known. However, as one skilled in the art will appreciate, platform area 110 poses certain structural challenges that make it difficult to cool it in this manner. Much of this is due to the unfavorable geometry of this area in the sense that the platform 110 as described is a peripheral component located away from the central core of the rotor blade and typically designed to have a structurally stable but thin radial Thickness.
    To recirculate a coolant, the rotor blades 100 typically include one or more hollow inner cooling channels 116 (see FIGS. 3, 4, 5, and 9) extending at least radially through the core of the blade 100, including through the foot 104 and Airfoil 102 extend therethrough. As will be described in more detail below, such inner cooling channels 116 may be configured to enhance heat exchange to have a serpentine path that passes through the central portions of the blade 100, although other configurations are possible. In operation, coolant may flow through one or more inlets 117 formed in the interior region of the foot 104 into the central internal cooling channels. The coolant may circulate through the blade 100 and exit through outlets (not shown) formed on the airfoil and / or through one or more outlets (not shown) formed in the base 104. The coolant may be pressurized and e.g. compressed air, compressed air mixed with water, steam and the like included. In many cases, the refrigerant is compressed air that is tapped from the compressor of the plant, although other sources are possible. As explained in more detail below, these internal cooling channels typically include a high pressure coolant area and a low pressure coolant area. The high pressure coolant area typically corresponds to an upstream portion of the inner cooling passage having a higher coolant pressure while the low pressure coolant area corresponds to a downstream area having a relatively lower coolant pressure.
    In some cases, the coolant from the inner cooling channels 116 may be directed into a cavity 119 formed between the shafts 112 and the platforms 110 of adjacent rotor blades 100. From there, the coolant may be used to cool the platform portion 110 of the blade, a conventional embodiment of which is shown in FIG. This type of construction typically draws air from one of the inner cooling channels 116 and uses the air to pressurize the cavity 119 formed between the shafts 112 and platforms 110. Once pressure has been applied to the cavity 119, it supplies coolant to the cooling channels extending through the platform 110. After traversing the platform 110, the coolant 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 contained in an element independently, because the refrigeration cycle is formed only when two adjacent rotor blades 100 have been assembled. This creates a considerable degree of difficulty and complexity in installation and flow testing prior to installation. A second disadvantage is that the integrity of the cavity 119 formed between adjacent rotor blades 100 depends on how well the periphery of the cavity 119 is sealed. Insufficient sealing can result in insufficient cooling of the platform and / or wasted cooling air. A third disadvantage is the inherent risk that gases from the hot gas path will penetrate into the cavity 119 or the platform 110 itself. This can happen if the cavity 119 is not kept under a sufficiently high pressure during operation. When the pressure of the cavity 119 drops below the pressure in the hot gas path, hot gases are drawn into the shaft cavity 119 or into the platform 110 itself, which typically damages these components because they are not designed to withstand the hot gas path conditions ,
    Figures 4 and 5 illustrate another type of conventional platform cooling design. In this case, the cooling circuit is contained in the rotor blade 100 and does not include the shaft cavity as shown. Cooling air is extracted from one of the inner cooling channels 116 extending through the core of the blade 110 and directed back through cooling channels 120 (i.e., "platform cooling channels 120") formed in the platform 110. As shown by a plurality of arrows, the cooling air flows through the platform cooling channels 120 and exits through outlets in the trailing edge 121 of the platform 110 or outlets disposed along the suction side edge 122. (Note that in describing or referring to the edges or surfaces of the rectangular platform 110, these may each be delineated depending on their location with respect to the suction surface 105 and the pressure surface 106 of the airfoil 102 and / or the plant directions front and rear Thus, as will be appreciated by those skilled in the art, the platform may include a trailing edge 121, a suction side edge 122, a leading edge 124, and a pressure side slot sidewall 126, as shown in Figures 3 and 4. In addition, Figs Suction side edge 122 and pressure side slot side wall 126 are also commonly referred to as "slot side walls", and the narrow cavity formed therebetween once adjacent rotor blades 100 have been installed may be referred to as a "slot sidewall cavity.")
    It will be appreciated that the conventional embodiments of FIGS. 4 and 5 have an advantage over the embodiment of FIG. 3 in that they are not affected by variations in assembly or installation conditions. However, the 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 thereby the disadvantage of limited control of the amount of cooling air used at various locations in the platform 110. Second, conventional designs of this type have a coverage area that is generally limited. While the serpentine path according to FIG. 5 represents an improvement in the sense of the cover with respect to FIG. 4, there are still dead areas in the platform 110 which remain uncooled. Third, in order to achieve better coverage with tangled platform cooling channels 120, manufacturing costs increase dramatically, especially when the cooling channels have shapes that require a molding process to form. Fourth, these conventional designs typically emit refrigerant after use and before it is completely consumed into the hot gas path, adversely affecting the efficiency of the plant. Fifth, conventional designs of this type generally have low flexibility. That is, the channels 120 formed as an integral part of the platform 110 have little or no possibility of changing their function or configuration as operating conditions change. Moreover, these types of conventional designs are difficult to repair and repair.
    As a result, conventional platform cooling designs are flawed in one or more important areas. It is therefore an object of the present invention to provide a turbine rotor blade having an improved platform cooling device and methods of manufacturing the same which effectively and efficiently cools the platform portion of the turbine rotor blade while being cost effective, flexible in use, and durable.
    Brief description of the invention
    This object is achieved by a turbine rotor blade with a platform cooling device according to claim 1.
    The invention further relates to a method for producing such a turbine rotor blade with a platform cooling device.
    These and other features of the present invention will become apparent upon review of the following detailed description of the preferred embodiments, taken in conjunction with the drawings and the appended claims.
    Brief description of the drawings
    These and other features of the invention will be more fully appreciated and understood from a study of the following more detailed description of exemplary embodiments of the invention taken in conjunction with the accompanying drawings.<Tb> FIG. FIG. 1 illustrates a perspective view of an exemplary turbine rotor blade in which embodiments of the present invention may be used; FIG.<Tb> FIG. FIG. 2 illustrates a bottom view of a turbine rotor blade in which embodiments of the present invention may be used; FIG.<Tb> FIG. 3 <SEP> is a sectional view of adjacent turbine rotor blades with a cooling system according to a conventional embodiment;<Tb> FIG. FIG. 4 illustrates a plan view of a turbine rotor blade having a platform with internal cooling passages according to a conventional embodiment; FIG.<Tb> FIG. FIG. 5 illustrates a plan view of a turbine rotor blade having a platform with internal cooling passages according to an alternative conventional embodiment; FIG.<Tb> FIG. FIG. 6 is a perspective view of a turbine rotor blade and a plate having a serpentine cooling passage according to an embodiment of the present invention; FIG.<Tb> FIG. Fig. 7 is a sectional plan view of a platform cooling device according to an embodiment of the present invention;<Tb> FIG. Fig. 8 is a perspective view of a plate having a serpentine cooling passage according to an embodiment of the present invention;<Tb> FIG. Fig. 9 is a sectional side view of an unchanged conventional platform in which embodiments of the present invention can be put into practice;<Tb> FIG. Fig. 10 is a sectional side view of the platform of Fig. 9 illustrating how the platform could be modified to accommodate an exemplary embodiment of the panel according to the present invention;<Tb> FIG. Fig. 11 is a sectional side view of the platform of Fig. 9 illustrating the panel when mounted to the modified platform of Fig. 10 in accordance with an exemplary embodiment of the present invention;<Tb> FIG. Fig. 12 is a perspective view of a plate having a serpentine cooling passage according to an alternative embodiment of the present invention;<Tb> FIG. Fig. 13 is a cross-sectional side view of a platform illustrating the plate of Fig. 12 when mounted in accordance with an alternative embodiment of the present invention; and<Tb> FIG. FIG. 14 shows an exemplary method for providing a platform cooling device according to an embodiment of the present invention.
    Detailed description of the invention
    Turbine rotor blades, which are cooled by internal circulation of a coolant, typically have an internal cooling passage 116 extending radially outwardly from the foot into the airfoil through the platform region, as discussed above in connection with various conventional cooling designs has been described. It will be appreciated that certain embodiments of the present invention may be used in conjunction with conventional coolant channels to enhance or facilitate effective active platform cooling, and the present invention will be described in connection with a common embodiment, an internal cooling channel 116 with a winding. or serpentine shape explained. As shown in FIGS. 6, 8, and 9, the serpentine path is typically configured to allow flow of coolant in one direction and has structures that promote heat exchange between the coolant and the surrounding rotor blade 100. In operation, pressurized coolant, which is typically compressed air bled from the compressor, is supplied to the inner cooling passage 116 through a connection formed through the foot 104 (although other types of coolant, such as steam, are also used with embodiments of the present invention could become). The pressure drives the coolant through the inner cooling passage 116, and the coolant absorbs heat by convection from the surrounding walls.
    As the coolant passes through the inner cooling passage 116, it will be appreciated that it will lose pressure so that the coolant in the upstream portions of the inner cooling passage 116 has a higher pressure than the coolant in the downstream portion. As explained in greater detail below, this pressure differential can be used to drive the coolant through internal cooling channels formed in the platform. It will be appreciated that the present invention may be used in rotor blades 100 having internal internal cooling channels of various configurations and is not limited to internal cooling channels having a serpentine shape. Accordingly, when used herein, the term "inner cooling channel" or "internal cooling channel" means that any passageways or hollow channels are included through which coolant can be circulated in the rotor blade. When provided herein, the inner cooling passage 116 according to the present invention extends at least to about the radial height of the platform 116 and may include at least a portion of relatively high coolant pressure (hereinafter referred to as a "high pressure region") and in some instances an upstream portion within a serpentine channel) and at least one region of relatively lower refrigerant pressure (hereinafter referred to as a "low pressure region" and with respect to the high pressure region may be a downstream portion within a serpentine channel).
    In general, the various designs of conventional internal internal cooling channels 116 are effective in providing active cooling for certain areas within the rotor blade 100. However, as one skilled in the art realizes, the platform area proves to be more challenging. This is due, in part, to the unfavorable geometry of the platform, i. its narrow radial height and the manner in which it protrudes from the core or main body of the rotor blade 100. However, when the effects of the extreme temperatures of the hot gas path and the high mechanical stresses experienced by the platform are present, the cooling requirements of the platform are significant. As described above, conventional platform cooling designs are ineffective because they do not address the specific challenges of the field, inefficient in their use of the coolant, and / or expensive to manufacture.
    Referring to Figs. 6-14, various views of exemplary embodiments of the present invention are shown. 6 shows a perspective view of a turbine rotor blade 100 and a plate 132 with a serpentine cooling channel 133 according to an embodiment of the present invention. As shown, the plate 132 may be attached to the platform 110. Specifically, the plate 132 may rest against the platform bottom 114. Like the top 113 of a platform 110, a platform bottom 114 may have an axially and circumferentially extending flat surface. (Note that the term "even" as used herein means approximately or substantially in the form of a plane, for example, one skilled in the art will recognize that platforms may be configured to have an outer surface that curves slightly and convex, the curvature corresponding to the circumference of the turbine at the radial position of the rotor blades When used herein, this type of platform shape is considered plane if the radius of curvature is sufficiently large to give the platform a flat appearance In one embodiment of the present invention, a flat pocket 131 may be disposed in the platform bottom 114, as shown in Figs. 9-11. The flat pocket 131 may be formed by one or more manufacturing methods, such as e.g. by machine or machining, casting and the like, but without being limited to these. An existing rotor blade may e.g. machined so that a suitable flat pocket is formed. In one embodiment of the present invention, the flat pocket 131 may be disposed at a portion of the platform lower surface 114 that substantially corresponds to the pressure side of the airfoil 102 of the airfoil 100. The flat pocket 131 according to the present invention may be configured to receive a plate 132.
    As shown in FIGS. 8 and 12, the plate 132 may have a radially thin structure with a flat top 134 on which the channel 133 is formed. The planar top surface 134 may extend in the axial and circumferential directions once attached to the platform bottom 114. In one embodiment, the channel 133 includes a serpentine or tortuous path, although other configurations are possible. As shown, the channel 133 is formed on the surface of the plate 132, i. not completely contained within the plate 132. The channel 133 can thus be described as remaining open at the top of the plate 134. It will be appreciated that platform bottom 114 includes channel 133 after attaching plate 132 to platform bottom 114. That is, platform bottom 114 for channel 133 may make a cover 140 once the two surfaces are joined.
    The channel 133 may have an upstream end 138 and a downstream end 139. A high pressure port 148 may connect the upstream end 138 of the passage 133 to the high pressure coolant portion of the inner cooling passage 116. A low pressure port 149 may connect the downstream end 139 of the channel 133 to the low pressure coolant portion of the inner cooling channel 116. With respect to the front and rear directions with respect to the rotor blade 100, the upstream end 138 of the channel 133 may have a relatively forward position and the downstream end 139 of the channel 133 may have a rearward position.
    As mentioned, the airfoil 102 may be described as having a pressure side 106 and a suction side 105, and a pressure-side slit sidewall 126 may include the platform edge corresponding to the pressure side 106 of the airfoil 102. In one embodiment, the plate 132 is disposed at a portion of the platform lower side 114 corresponding to the pressure side of the airfoil, as shown in FIG. Furthermore, as shown in Figs. 7, 8 and 12, the plate 132 may be in profile, i. 7, have a curved edge 151 and a straight edge 152. It will be appreciated that the arcuate edge 151 in shape approximates the curved profile of the airfoil 102, while the pressure side 106 of the airfoil 102 connects to the platform 110. On the other hand, the straight edge 151 in the shape can approximately correspond to the straight-line profile of the pressure-side slotted side wall 126. Specifically, the arrangement of the arcuate edge 151 and the straight edge 152 of the plate 132 may, in some embodiments, correspond to the arrangement of the curved profile of the airfoil 102 and the rectilinear profile of the pressure-side slot sidewall 126.
    In some embodiments, the channel 133 is configured to include a slot sidewall portion 155. The slot sidewall portion 155 may include a portion of the channel that is proximate and parallel to the straight edge 152 of the panel 132 (and thus located near the pressure-side slot sidewall 126 as shown in FIG. 7 when the panel 132 is installed is). The upstream end 138 of the slit sidewall portion 155 may be located near the upstream end 138 of the channel 133. The length that the slot sidewall portion 155 extends along the straight edge 152 of the panel 132 may be referred to as a "slot sidewall portion channel length". In preferred embodiments, the slot sidewall portion channel length may be at least 0.5 times the length of the slot sidewall 126. More preferably, the slot sidewall portion channel length may be greater than 0.75 times the length of the slot sidewall 126. It will be appreciated that locating this portion of the channel in this manner provides certain efficiency benefits. Because the slot sidewall portion 155 is located near the upstream end 138 of the conduit 133, the coolant supplied must be e.g. flow through this area first, causing it to receive coolant at a lower temperature than downstream portions of the channel 133. If this is a platform area that is exposed to some of the highest operating temperatures and is a traditionally difficult to cool area because it is remote from the central areas of the rotor blade 100, targeting that area will result in a desired cooling strategy.
    After the slot sidewall portion, the channel 133 has a turn 158 (ie, a sharp curve of about 180 °) and extends following the turn 158 into the central portions of the plate 132, which serves as an inner portion 159 of the channel 133 can be designated. The inner portion 159 may include a rectilinear portion downstream of the first turn 158 and downstream thereof a second turn 158, the combination of which effectively provides coverage of the central portions of the plate 132. The second turn 158 may be near the downstream end 139 of the passage 133.
    In some embodiments, the upstream end 138 of the channel 133 has an upstream chamber. Generally, the upstream chamber 138 has an area with an increased channel width. As shown, the upstream chamber 138 may be circular in profile. In operation, the upstream chamber 138 creates a large volume where multiple coolant supply lines (if present) may be collected and thereafter fed into the channel 133. Also, the upstream chamber 138 forms a larger target profile through which the connection to the high pressure port 148 can be made. Similarly, the downstream end 139 of the channel 133 has a downstream chamber in some embodiments. Generally, the downstream chamber 139 also includes an area of increased channel width and the downstream chamber 139 may have a circular profile as shown. The downstream chamber 139 creates a larger target profile through which the connection to the low pressure port 149 can be made.
    As mentioned, the high pressure port 148 is connected to the upstream end 138 of the passage 133, and the low pressure port 149 is connected to the downstream end 139 of the passage 133. The connection can be made using various configurations. For example, in a preferred embodiment (as shown in FIG. 8), the plate 132 has an outer sidewall 144 that extends uninterruptedly around the circumference of the plate 132. In this case, as shown in FIGS. 9 to 11, the terminals 148, 149 include a portion internally formed with the blade 100 and a bottom channel 161 formed on the platform 110. In detail, the lower side channel 161 has a channel formed on the surface of the platform lower side 114. It will be appreciated that the bottom channel 161, similar to the channel 163, remains open at the surface to which it is located, which in this case is the platform bottom 114. The bottom channel 161 is not closed until the plate 132 is attached to the platform 110. It will be appreciated that the top plate 134 may be described as acting as a bottom 162 of the bottom channel 161 once the plate 132 has been mounted. As noted, this configuration may be used on both the high pressure port 148 and the low pressure port 149. In the case of the high-pressure port 148, the downstream end of the lower-side passage 161 is capable of the upstream end of the passage 133, each offset in the radial direction. In the case of the low-pressure port 149, the upstream end of the lower-side passage 161 is in the position of the downstream end 139 of the passage 133, each offset in the radial direction.
    In another embodiment, the outer sidewall 144 may include a sidewall inlet 165 and a sidewall outlet 166 formed through the outer sidewall 144, as shown in FIG. 12. In this case, the sidewall inlet 165 may connect the upstream end 138 of the channel 133 directly to the high pressure port 148 through the outer sidewall 144. The sidewall outlet 166 may directly connect the downstream end 139 of the channel 133 to the low pressure port 149 via the outer sidewall 144.
    The plate 132 may be attached to the platform bottom 114 using a variety of techniques. In some embodiments, the plate 132 is removably attached to the platform 110. When this term is used, it is meant that this type of connection includes any attachment that can be reasonably undone so that the plate 132 and / or the blade 100 can be reused. This can e.g. certain types of welding and brazing, as well as certain types of adhesives, mechanical supports and the like. As part of mounting the plate, conventional steps may be taken to seal the formed channel 133, and the connections that it makes to the ports 148, 149 may result in substantially a closed coolant loop between the high pressure port 148 and the low pressure port 149. Thus, substantially all of the coolant flowing from the high pressure port 148 into the passage 133 is returned to the inner cooling passage 116 via the low pressure port 149 for further use. Those skilled in the art will recognize that any sealing device could be used between the plate 132 and the platform bottom 114. It could e.g. a mechanical sealing washer, a chemical sealant and the like may be used.
    The platform cooling device 130 can be used to efficiently retrofit existing turbine rotor blades because the plate 132 and the platform 110 are not integral components. The platform cooling device 130 uses existing internal cooling channels 116 of the turbine rotor blades 110, which provides the flexibility to use embodiments of the present invention in existing or new blades. The plate 132 is also adaptable by modifications after casting. Various aspects of the plate 132 and the channel 133 may be modified to optimize the cooling of the platform 110. Thus, the platform cooling device 130 may be tailored to suit a variety of turbine rotor blade configurations. The platform cooling device 130 can also be manufactured inexpensively and efficiently because the plate 132 can be manufactured separately from the various components of the turbine rotor blades. In addition, the plate 132 may be prefabricated and then mounted on site.
    FIG. 14 illustrates a flowchart 200 illustrating an exemplary method of providing the turbine rotor blade 100 with platform cooling device 130 according to an embodiment of the present invention. Flowchart 200 begins at a step 202 where the flat pocket 131, if required, is machined into the platform bottom 114 at a predetermined location. In some embodiments, the preferred location corresponds to the pressure-side slot sidewall 126. This machining operation is illustrated in FIGS. 9-11. Fig. 9 illustrates the cross-section of a platform 110 before the pocket 131 has been formed. As shown, numerous existing platforms 110 may have a flat bottom 114, however, some machining may be required to provide sufficient clearance for a plate 132 that is sized to provide a desired coverage area of the cooling. Fig. 10 illustrates the areas that may be provided for removal. The flat pocket 131 may have a profile shape which substantially corresponds to the profile of the pressure side 106 of the airfoil 102, which may also correspond to the profile of the shaped plate 132. It will be appreciated that the flat pocket 131 may already be present in the bucket 100 as a cast-in element in some cases.
    In step 204, the high pressure port 148 and the low pressure port 149 may be formed. The high pressure port 148 may have a predetermined configuration and location so that it connects the high pressure coolant portion of the inner cooling channel 116 to the final position of the upstream end 138 of the plate channel 133 or sidewall inlet 165 of the plate 132, whichever the case may be. In the case where the side inlet 165 is absent, the formation of the high pressure port 148 may include the formation of a bottom channel 161 as described above. Likewise, the low pressure port 149 may have a predetermined configuration and location so as to connect the low pressure coolant portion of the inner cooling channel 116 to the final position of the downstream end 139 of the plate channel 133 or sidewall outlet 166, whichever the case may be. In the case where the sidewall outlet 166 is not present, the formation of the low pressure port 149 may include the formation of a bottom channel 161 as described above. It will be appreciated that the formation of the terminals 148, 149 may be completed using a relatively inexpensive machining process, particularly if there is access available to the relevant area of the blade 100 after the formation of the flat pocket 131 is completed and before the plate 132 is attached.
    In step 206, the plate 132 can be manufactured according to desired specifications. It will be appreciated that the separate manufacture of the plate 132 simplifies the manufacturing process. The channel 133 may be e.g. be formed on the plate 132 using simple machining processes or casting techniques. In contrast, forming the same channel within an integrally formed platform would typically require a much more complicated and expensive casting operation.
    In a step 208, the plate 132 may be attached to the platform bottom 114 so that the plate 132 is located within the platform bottom 114, thereby closing the channel 133 between the plate 132 and the platform bottom 114. The plate 132 may be attached to the platform bottom 114 so that the plate 132 lies in the flat pocket 131. Finally, in step 210, further steps may be taken to seal the channel 133. As noted, sealing the channel 133 and the connections it forms with the ports 148, 149 substantially results in a closed coolant loop between the high pressure port 148 and the low pressure port 149. It will be appreciated that the present invention benefits from centrifugal loading which occurs during operation to enhance the sealing effect created between the plate 132 and the platform bottom 114, particularly when one or more bottom channels 161 are used to connect the channel 133 to the coolant supply.
    A turbine rotor blade is provided with a platform cooling device 130, wherein the turbine rotor blade has a platform at a transition between an airfoil 102 and a foot 104 and a cooling passage 116 which in use has at least one high pressure coolant area and one low pressure coolant area Platform bottom 114 has. The platform cooling device 130 includes: a plate 132 having a plate top; a channel 133 formed on the top of the plate, the channel 133 having an upstream end 138 and a downstream end 139 and being open on the top of the plate such that the platform bottom includes a channel cover 140 when the plate 132 is attached to the platform 110; a high pressure port 148 connecting the upstream end 138 of the passage 133 to the high pressure coolant portion of the inner cooling passage 116; and a low pressure port 149 connecting the downstream end 139 of the passage 133 to the low pressure coolant portion of the inner cooling passage 116.
    权利要求:
    Claims (12)
    [1]
    A turbine rotor blade (100) having a platform cooling device (130), the turbine rotor 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 rotor blade (100) and relating to the installed state of the turbine rotor blade (100) in a turbine from connection to a source of coolant at the foot (104) to at least the radial height of the platform (110) wherein the cooling channel (116) has at least one high-pressure coolant area and one low-pressure coolant area in operation,wherein the platform (110) has a radially inwardly facing platform underside (114) in a turbine along a radially inwardly facing surface with respect to the installed state of the turbine rotor blade (100) in a turbine,wherein the platform cooling device (130) comprises:a plate (132) having a radially outwardly facing plate top surface (134) relative to the installed state of the turbine rotor blade (100) in a turbine, the plate top side (134) being detachably connected to the platform bottom (114),a channel (133) formed on the plate top (134), the channel (133) having an upstream end (138) and a downstream end (139) with respect to the installed state of the turbine rotor blade (100) in a turbine; Top plate (134) is open so that the platform bottom (114) forms a channel cover (140) upon attachment of the plate (132) to the platform (110);a high pressure port (148) connecting the upstream end (138) of the channel (133) formed in the plate top (134) to the high pressure coolant portion of the cooling channel (116); anda low pressure port (149) connecting the downstream end (139) of the channel (133) formed in the plate top (134) to the low pressure coolant portion of the cooling channel (116).
    [2]
    A turbine rotor blade (100) according to claim 1, wherein:the plate (132) and the platform (110) are separately formed components of the turbine rotor blade (100);the platform (110) has a planar radially outwardly facing upper surface and a radially inwardly facing planar lower surface relative to the installed state of the turbine rotor blade (100) in a turbine; the cooling channel (116) has a serpentine shape; and the high pressure refrigerant area is an upstream portion of the cooling passage (116) with respect to a refrigerant flow direction in which refrigerant flows through the cooling passage (116) and the low pressure refrigerant area forms a downstream portion of the cooling passage (116).
    [3]
    A turbine rotor blade (100) according to claim 1, wherein:the platform lower side (114) has a flat surface extending axially and circumferentially with respect to the installed state of the turbine rotor blade (100) in a turbine;the plate top surface (134) has a planar surface extending axially and circumferentially with respect to the installed state of the turbine rotor blade (100) in a turbine;the channel (133) formed in the plate top (134) includes a serpentine channel;the airfoil (102) has a pressure side (106) and a suction side (105);a pressure-side slot side wall (126) of the turbine rotor blade (100) with respect to the airfoil (102) has a pressure-side platform edge with respect to the airfoil (102);the plate (132) is disposed in a pressure-side region of the platform lower side (114) with respect to the airfoil (102); andthe upstream end (138) of the channel (133) formed in the top surface (134) has a front position and the downstream end (139) of the channel (133) formed in the top surface (134) has a rearward position with respect to the front and rear Direction of the rotor blade (100).
    [4]
    A turbine rotor blade (100) according to claim 3, wherein said plate (132) has a profile with a curved edge (151) and a rectilinear edge (152) in a radial top view radially of a state of installation of the turbine rotor blade (100). wherein the arcuate edge (151) in the shape approximates the curved profile of the airfoil (102) where the airfoil (102) joins the platform (110), and wherein the rectilinear edge (152) is approximately in the shape of the rectilinear profile the pressure side slot side wall (126) corresponds;wherein in a turbine radial projection with respect to the state of installation of the turbine rotor blade (100), the arrangement of the arcuate edge (151) and straight edge (152) of the plate (132) relative to the arrangement of the curved profile of the airfoil (102) and the straight-line profile of the pressure-side slot side wall (126) is arranged offset; andthe channel (133) formed in the disc top (134) has a slot sidewall portion (155) facing the slot sidewall (126), the slot sidewall portion (155) comprising a portion of the channel (133) formed in the disc top (134) adjacent thereto and parallel to the rectilinear edge (152) of the plate (132).
    [5]
    A turbine rotor blade (100) according to claim 4, wherein the upstream end of the slot sidewall portion (155) is located in an area adjacent to the upstream end (138) of the channel (133) formed in the disc top (134);wherein the length over which the slot sidewall portion (155) extends adjacent to and parallel to the rectilinear edge (152) of the panel (132) has a slot sidewall portion channel length; wherein the slot sidewall portion channel length is greater than 0.75 times the length of the pressure-side slot sidewall (126);wherein the channel (133) formed in the plate top (134) has a first turn (158) after the slot sidewall portion (155) and an inner portion (159) downstream of the first turn (158) located in the central portion of the plate (15). 132) is arranged;wherein said inner portion (159) has a rectilinear portion disposed immediately downstream of said first turn (158) and a second turn (158) disposed downstream of said straight portion; andwherein the second turn (158) is disposed in an area adjacent to the downstream end (139) of the channel (133) formed in the plate top (134).
    [6]
    A turbine rotor blade (100) according to claim 5, wherein:the upstream end (138) of the channel (133) formed in the top surface (134) has an upstream chamber (138) with an increased channel width;the downstream end (139) of the channel (133) formed in the top surface (134) has a downstream chamber (139) having an increased channel width; andthe high pressure port (148) is connected to the upstream chamber and the low pressure port (149) is connected to the downstream chamber.
    [7]
    A turbine rotor blade (100) according to claim 1, wherein the plate (132) has a peripheral side wall (144), the peripheral side wall (144) being a solid wall extending continuously around the circumference of the plate (132) ;wherein the high pressure port (148) has a first bottom channel (161) formed on the platform bottom (114), the first bottom channel (161) being open at the platform bottom (114) such that the top surface (134) is for at least one Portion of the first bottom channel (161) forms a bottom channel bottom (162) when the plate (132) is attached to the platform bottom (114); andwherein the low pressure port (149) has a second bottom channel (161) formed on the platform bottom (114), the second bottom channel (161) being open at the platform bottom (114) such that the top surface (134) is at least one Section of the second bottom channel (161) forms a bottom channel bottom (162) when the plate (132) is attached to the platform (110).
    [8]
    A turbine rotor blade (100) according to claim 7, wherein the downstream end of the first sub-side channel (161) in a turbine with respect to the installation state of the turbine rotor blade (100) is the upstream end (138) of the channel (133) formed in the plate top (134). at least partially axially and circumferentially overlapping, which are each offset in the radial direction against each other; andwherein the upstream end of the second lower side passage (161) at least partly axially and circumferentially overlaps the downstream end (139) of the channel (133) formed in the upper plate (134) with respect to the installed state of the turbine rotor blade (100) in a turbine the radial direction are offset from each other.
    [9]
    The turbine rotor blade (100) of claim 1, wherein the plate (132) has a peripheral side wall (144), the peripheral side wall (144) having a sidewall inlet (165) and a sidewall outlet (166) extending therethrough extend;the sidewall inlet (165) being adapted to connect the upstream end (138) of the channel (133) formed in the plate top (134) to the high pressure port (148); andwherein the sidewall outlet (166) is configured to connect the downstream end (139) of the channel (133) formed in the plate top (134) to the low pressure port (149).
    [10]
    10. A method of manufacturing a turbine rotor blade (100) having a platform cooling device (130) according to claim 1, said method comprising the steps of:machining the high pressure port (148);machining the low pressure port (149);Attaching the top (134) of the panel (132) to the platform bottom (114) such that the platform bottom (114) forms the channel cover (140) after attaching the panel (132) to the platform (110);wherein the channel (133) formed in the plate top (134) includes a serpentine channel.
    [11]
    11. The method of claim 10, wherein the plate (132) has a profile with a curved edge (151) and a rectilinear edge (152) in a plan view radial with respect to the installed state of the turbine rotor blade (100) in a turbine, wherein the bent edge (151) coincides in shape approximately with the curved profile of the airfoil (102) where the airfoil (102) connects to the platform (110); the method further comprising the steps of:machining a pocket (131) in the platform underside (114) at a pressure side relative to the airfoil (102), the pocket (131) having a profile shape corresponding to the profile of the panel (132); andSealing the channel (133) formed in the plate top surface (134) such that in operation substantially all of the refrigerant is returned to the cooling channel (116) through the channel (133) formed in the plate top surface (134);wherein the plate (132) is attached to the platform bottom (114) such that the plate (132) is disposed in the pocket (131).
    [12]
    The method of claim 11, wherein the channel (133) formed in the top surface (134) includes a slot side wall portion (155), the slot side wall portion (155) including a portion of the channel (133) formed in the top surface (134) in the vicinity of and parallel to the rectilinear edge (152) of the plate (132), and the upstream end of the slit sidewall portion (155) in an area adjacent to the upstream end (138) of the channel formed in the plate top (134) (133) is arranged.
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    同族专利:
    公开号 | 公开日
    CH703877A2|2012-03-30|
    JP2012077748A|2012-04-19|
    DE102011053874A1|2012-04-05|
    CN102444429B|2015-04-08|
    JP5898901B2|2016-04-06|
    US20120082549A1|2012-04-05|
    CN102444429A|2012-05-09|
    US8777568B2|2014-07-15|
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    法律状态:
    2017-03-15| NV| New agent|Representative=s name: GENERAL ELECTRIC TECHNOLOGY GMBH GLOBAL PATENT, CH |
    2021-04-30| PL| Patent ceased|
    优先权:
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    US12/894,993|US8777568B2|2010-09-30|2010-09-30|Apparatus and methods for cooling platform regions of turbine rotor blades|
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