• 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 has a platform, a platform cooling device and a cooling channel (116) formed therein. The platform cooling device (130) further includes: a main channel (132) disposed radially further inward relative to the installed state of the turbine rotor blade (100) in a turbine with respect to the planar top surface and extending within the pressure side and / or suction side of the platform axially downstream position to an axially upstream position, the main channel (132) having a longitudinal axis that is approximately parallel to the planar top surface; a feed channel (134) extending between the main channel (132) and the cooling channel (116); and a plurality of cooling holes (136), each cooling hole (136) extending away from the pressure side and / or suction side slot sidewalls (126, 122) to communicate with the main channel (132).
    公开号:CH703894B1
    申请号:CH01600/11
    申请日:2011-09-28
    公开日:2016-05-13
    发明作者:Edmond Ellis Scott；Alan Hynum Daniel；Wesley Harris John Jr
    申请人:Gen Electric；
    IPC主号:
    专利说明:

    Background of the invention
    The present invention is a turbine rotor blade with a platform cooling device and a method for their preparation.
    A gas turbine typically includes a compressor, a burner and a turbine. The compressor and turbine generally include rows of blades or blades arranged axially in steps one behind the other. Each stage typically includes a series of circumferentially spaced rotor blades that are fixedly disposed and a set of circumferentially spaced rotor blades that rotate about a central axis or shaft. In operation, the rotor blades of the compressor are rotated about the shaft to compress an airflow. The compressed air is then used in the burner to burn supplied fuel. The hot gas stream resulting from the combustion process is then expanded as it passes through the turbine causing the rotor blades to rotate the shaft to which they are attached. In this way, the energy contained in the fuel is converted into the mechanical energy of the rotating shaft, which can then be used for example to drive generator coils to generate electricity.
    Reference is made to FIGS. 1 and 2; The rotor blades 100 of the turbine generally include a blade section or blade 102 and a root section or root 104. The blade 102 has a convex suction surface 105 and a concave pressure surface 106. The blade 102 also has a leading edge 107 which is the leading edge and a trailing edge 108 which is the trailing edge. The foot 104 has a structure (which typically includes a dovetail 109, as shown) for securing the blade 100 to the rotor shaft, a platform 110 from which the blade 102 extends away, and a shank 112 which defines the structure between the shaft Dovetail 109 and the platform 110 includes.
    As shown, the platform 110 may be substantially planar. Specifically, the platform 110 may have a planar top surface 113 which, as illustrated in FIG. 1, has an axially and circumferentially extending flat surface. As illustrated in FIG. 2, the platform 110 may include a planar bottom surface 114 which also has an axially extending and circumferentially extending flat surface. The top 113 and the bottom 114 of the platform 110 may be formed to be oriented substantially parallel to one another. As illustrated, it can be seen that the platform 110 typically has a thin radial profile, that is, there is a relatively small radial distance between the top 113 and the bottom 114 of the platform 110.
    Generally, the platform 110 on a turbine rotor blade 100 is used to form the inner flow path boundary of the hot gas path portion of the gas turbine. The platform 110 also provides structural support to the blade 102. In operation, the rotational speed of the turbine causes a mechanical stress that creates high stress areas along the platform 110 such that, in conjunction with high temperatures, operational failures may eventually occur, such as oxidation, creep , Fatigue fractures at low load cycles and the like. Of course, these defects negatively impact the useful life of the rotor blade 100. It can be seen that these harsh operating conditions, i. exposure to high temperatures of the hot gas path and mechanical loading applied to the rotating blades poses a significant challenge in designing durable, durable rotor blade platforms 110 that are both benign and cost-effective to manufacture.
    A common solution to make platform section 110 more durable is to cool it during operation with a flow of compressed air or other coolant, a variety of such designs being known. However, those skilled in the art will understand that the platform portion 110 poses a certain design challenge that makes it difficult to cool it in this manner. Much of this is due to the awkward geometry of this region due to platform 110 being a peripheral component located away from the central core of the rotor blade and typically arranged thereon, of structurally sound but radially small thickness to have.
    For directing the coolant, the rotor blade 100 typically has one or more cooling channels 116 (see FIGS. 3, 4, 5, and 9) that extend radially at least through the core of the blade 100 including the foot 104 and the blade 102 , As will be described in more detail below, such cooling channels 116 may be formed to increase heat exchange in the form of serpentines winding through the central portions of the blade 100, although other configurations are possible. During operation, coolant may flow into the central cooling channels via one or more inlets 117 formed in the inlet portion of the foot 104. The coolant may circulate through the blade 100 and exit through outlets (not shown) formed on the blade and / or through one or more outlets (not shown) formed in the foot 104. The coolant may be under pressure such as compressed air, compressed air mixed with water, steam or the like. In many cases, the refrigerant is compressed air that has been tapped from the compressor of the gas turbine, although other sources are possible. As described in more detail below, the cooling channels typically include a high pressure cooling region and a low pressure cooling region. The high-pressure cooling zone typically corresponds to an upstream section of the cooling channel, which has a higher coolant pressure, whereas the low-pressure cooling zone corresponds to a downstream section, in which a comparatively lower coolant pressure prevails.
    In some cases, the coolant may be directed out of the cooling channels 116 into a cavity 119 formed between the shafts 112 and 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 design of which is illustrated in FIG. In this design, air is typically extracted from one of the cooling channels 116, and the air is used to pressurize the cavity 119 formed between the shafts 112 and platforms 110, respectively. Once pressurized, the cavity 119 then delivers coolant to cooling channels that extend through the platforms 110. After traversing 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 is understood that this type of conventional design has several disadvantages. First, the cooling circuit is not completely formed in one part, because the cooling circuit is formed only after two adjacent rotor blades 100 are assembled. This leads to high demands and complexity in terms of installation and flow tests before 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. A poor seal can mean insufficient platform cooling and / or cooling air loss. A third disadvantage is the inherent risk that hot gas path gases will be sucked into the cavity 119 or the platform 110 itself. This can be done if the cavity 119 is not maintained at a sufficiently high pressure during operation. When the pressure in the cavity 119 drops below the pressure prevailing in the hot gas path, hot gases enter the stem cavity 119 or the platform 110 itself, which typically damages these components, because they are not designed to be permanently exposed to the conditions in the hot gas path ,
    Figures 4 and 5 illustrate another type of conventional platform cooling design. In this case, the refrigeration cycle is included in the rotor blade 100 and, as shown, does not include a stem cavity 119. Cooling air is removed from one of the cooling channels 116 extending through the core of the blade 110 and through cooling channels 120 formed in the platform 110 are formed (ie, "platform cooling channels 120") directed backwards. As indicated by various 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 formed along the suction edge 122. (It is noted that in describing or referring to edges or surfaces of the rectangular platform 110, any may be described based on their arrangement with respect to the suction surface 105 or pressure surface 106 of the blade 102 and / or the front and rear directions of the gas turbine, As far as the bucket 100 is installed, the platform can, as one skilled in the art will appreciate, have a trailing edge 121, a suction side edge 122, a leading edge 124, and a pressure side edge 126, as indicated in Figures 3 and 4. In addition, the suction side edge 122 can and the pressure-side edge 126 may be referred to as "slot sidewalls", where the cavity formed between them when adjacent rotor blades 100 are installed may be referred to as a "slot cavity.")
    It will be appreciated that the conventional structures of Figs. 4 and 5 have an advantage over the structure of Fig. 3 in that they are not affected by variations in assembly or installation conditions.
    However, conventional designs of this type have various limitations and disadvantages. First, as shown, only one circuit is provided on each side of the blade 102, and thus there is the disadvantage of limited control of the amount of cooling air used at various locations on the platform 110. Second, conventional designs of this type have a coverage area that is generally limited. While the serpentine tortuous path of FIG. 5 is an improvement over the cover of FIG. 4, dead zones still exist in the platform 110 which remain uncooled. Third, manufacturing costs dramatically increase when, to achieve better coverage with internally formed platform cooling channels 120, the cooling channels have particular shapes that require a molding process to form them. Fourth, these conventional designs typically discharge coolant after use and before full utilization of the coolant in the hot gas path, adversely affecting the efficiency of the gas turbine. Fifth, designs of this kind generally have little flexibility. This means that the channels 120 are formed as an integral part of the platform 110 and leave 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 repair.
    As a result, conventional platform cooling structures have disadvantages in one or more areas.
    The object of the present invention is therefore to provide a turbine rotor blade with an improved platform cooling device and method for their production, which allows effective and efficient cooling of the platform portion of the turbine rotor blade and at the same time cost-effectively produce and 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.
    Brief description of the drawings
    The invention will be more fully understood from the following detailed description of exemplary embodiments of the invention, taken in conjunction with the accompanying drawings, in which:<Tb> FIG. 1 <SEP> illustrates a perspective view of an exemplary turbine rotor blade in which embodiments of the present invention may be utilized;<Tb> FIG. Figure 2 illustrates a bottom view of a turbine rotor blade in which embodiments of the present invention may be used;<Tb> FIG. FIG. 3 illustrates a cross-sectional view of adjacent turbine rotor blades having a cooling system according to a conventional construction; FIG.<Tb> FIG. Figure 4 illustrates a plan view of a turbine rotor blade having a platform with internal cooling passages according to a conventional construction;<Tb> FIG. 5 illustrates a plan view of a turbine rotor blade having a platform with internal cooling passages according to an alternative conventional design;<Tb> FIG. Figure 6 illustrates a perspective view of a platform cooling device according to an exemplary embodiment of the present invention;<Tb> FIG. FIG. 7 illustrates a partially sectioned plan view of a platform of a turbine rotor blade having a cooling arrangement according to an exemplary embodiment of the present invention; FIG.<Tb> FIG. Figure 8 illustrates a front view from a viewpoint along lines 8-8 of Figure 7;<Tb> FIG. Fig. 9 <SEP> illustrates a cross-sectional view taken along line 9-9 in Fig. 7;<Tb> FIG. Fig. 10 illustrates a partially sectioned plan view of a turbine rotor blade with a platform cooling device according to an alternative embodiment of the present invention; and<Tb> FIG. 11 illustrates an exemplary method of creating a platform cooling device according to an exemplary embodiment of the present invention.
    Detailed description of the invention
    It is understood that turbine blades cooled by the internal circulation of a coolant typically have an internal cooling channel 116 extending radially outwardly from the foot through the platform portion and into the blade portion, as described above with respect to various conventional cooling structures is described. It should be understood that certain embodiments of the present invention may be utilized in conjunction with conventional cooling channels to enhance or facilitate efficient active platform cooling, with the present invention being discussed in conjunction with a conventional configuration, namely, an inner cooling channel 116, that winds or runs as a serpentine. As illustrated in FIG. 7, the serpentine pathway is typically configured to permit unidirectional coolant flow and contain structural details that promote heat exchange between the coolant and the surrounding rotor blade 100. During operation, a pressurized refrigerant, which is typically compressed air bled from a compressor (other types of refrigerant, such as steam, may be utilized in various embodiments of the present invention), may be passed through a passageway 104 through the foot 104 the interior of the cooling channel 116 are passed. The pressure drives the coolant through the inner cooling passage 116 and the coolant absorbs heat from the surrounding walls.
    As will be appreciated, as the coolant passes through the cooling passage 116, the coolant loses pressure so that the coolant in the upstream portions of the internal cooling passage 116 has a higher pressure than the coolant in downstream portions. As discussed in greater detail below, this pressure differential may be used to propel the coolant over or through cooling channels formed in the platform. It will be appreciated that the present invention may be used on rotor blades 100 which have internal cooling channels of different configurations and are not limited to internal serpentine cooling channels. Accordingly, as used herein, the term "inner cooling channel" or "cooling channel" includes any passage or channel through which coolant can be directed within the rotor blade. As anticipated herein, the internal cooling passage 160 of the present invention extends at least approximately to the radial position of the platform 116 and may include at least a portion of comparatively higher coolant pressure (hereinafter referred to as the "high pressure section", which in some instances is an upstream section within one Serpentine channels) and at least a portion of relatively lower refrigerant pressure (hereinafter referred to as "low pressure section" and which may be a downstream region relative to the high pressure section within a serpentine channel).
    In general, the various configurations of conventional internal cooling channels 116 are effective in providing active cooling for particular areas within the rotor blade 100. However, as the person skilled in the art knows, the platform areas prove to be more difficult. This is at least partially due to the difficult platform geometry, i. its small radial height and the way in which it is away from the core or main body of the rotor blade 100. Given the high temperatures to which it is exposed in the hot gas path and the high mechanical stress, the cooling requirements of the platform are quite considerable. As described above, conventional platform cooling designs are ineffective because they do not address the specific challenges of this area, are inefficient in terms of coolant utilization, and costly to manufacture.
    Reference is now made to Figs. 6 to 11, which illustrate various views of exemplary embodiments of the present invention. In particular, FIGS. 6-9 illustrate a rotor blade 100 having a platform cooling device 130 according to an embodiment of the present invention. As illustrated, the rotor blade 100 includes a platform 110 disposed at the junction between an airfoil 102 and a foot 104. The rotor blade 100 has an inner cooling channel 116 that extends from the root 104 to at least approximately the radial height of the platform 110 and, in most instances, into the airfoil 102 with respect to the installed state of the turbine rotor blade 100 in a turbine. As can be seen, on the side of the platform 110 which coincides with a pressure surface 106 of the airfoil 102, the platform 110 may have a planar top surface 113 extending from the airfoil 102 to a pressure-side slit sidewall 126. It should be noted that "planar" as used herein means approximately or substantially the shape of a plane. For example, it will be appreciated by those skilled in the art that platforms may have an outboard surface that is slightly curved or convex, the curvature corresponding to the circumference of the turbine and the radial position of the rotor blades. As used herein, this type of platform shape is considered planar because the radius of curvature is sufficiently large to give the platform a flat appearance. In addition, in the interior of the platform 110, in an exemplary embodiment of the present invention, a main channel 132; a supply passage 134 connecting the main passage 132 with the inner cooling passage 116; and a number of cooling holes 136 through which coolant may be distributed over the interior portions of the platform 110.
    Attention may be directed to the main channel 132, which may be formed inwardly with respect to the planar top surface 113 and which may be referred to as the rearward or rearward location with respect to the installed state of the turbine rotor blade 100 in a turbine from an axially downstream location. to an axially upstream location, hereinafter sometimes referred to as a front location, along the pressure side slot sidewall 126, although of course the main channel 134 as well as the other details described herein may equally be formed on the suction side 110 and along the suction side slot sidewall. Additionally, the main channel 132 may be oriented parallel to the platform 110, as shown, and that is, the main channel 132 may be a long and relatively narrow channel and have a longitudinal axis oriented parallel to the planar top surface. In one embodiment, the main channel 132 arcuates from a rearward position to a forward position on the pressure side slot sidewall 126. As viewed from the pressure side of the platform 110, the arc may be concave. As more clearly shown in Fig. 7, the curvature of the arc may correspond to the profile of the contour of the pressure surface 106 of the airfoil 102 (i.e., corresponding to the shape of the airfoil 102, as viewed from the perspective 107). More specifically, the arc may have approximately the same shape as the pressure surface 106 of the airfoil 102 at the location where the pressure surface 106 of the airfoil 102 intersects the platform 110. It will be understood that this preferred arrangement provides exceptional coolant distribution and coverage, as discussed in more detail below. In preferred embodiments, the main channel 132 is shaped to extend over a substantial portion of the platform 110. One way in which this can be defined is to compare the axial length of the main channel 132 with the axial length of the airfoil 102. In preferred embodiments, the main channel 132 has an axial length of at least 0.75 of the axial length of the airfoil 102 Type of axial length provides a favorable coolant distribution over the entire interior of the platform 110 along the pressure side of the rotor blade. In some embodiments, the main channel 132 includes a main channel outlet 133 at one or more locations along the pressure-side slot sidewall 126. In one preferred embodiment, the main channel 132 may have a main channel outlet 133 at a rearward position on the pressure-side slot sidewall 126, as shown, and another Main duct outlet 133 at a front position on the pressure-side slot side wall 126 have. Each of the main channel outlets 133 may be formed to have a flow cross-sectional area that is smaller than the flow cross-sectional area of the main channel, as shown. As discussed in greater detail below, this may be so for various reasons. First, the flow cross-sectional area may be reduced to eject the coolant exiting through these outlets. As those skilled in the art will appreciate, this may result in the exiting coolant having a desired coolant impact characteristic, such as a desired coolant pressure. an increased coolant exit velocity, so that the cooling effect of the resulting coolant flow is increased.
    Second, the flow cross-sectional area of the main channel outlets 133 can be reduced in terms of the size of the main channel and the need to evenly distribute the coolant over the entire interior of the platform 110. That is, the main channel 132 is configured to distribute low pressure loss refrigerant to the various cooling holes 136. To accomplish this, the flow area of the main channel 132 is typically significantly larger than the flow area of the cooling holes 136.
    It is understood that if the main duct outlets 133 are not reduced in size compared to the main duct 132, an excessive amount of coolant would exit the platform 110 through the main duct outlet 133 and the supply of coolant available to the cooling holes 136 would be, would be inadequate. The Hauptkanalauslässe 133 can thus be sized in size so that they have a flow cross-sectional area, which provides a desired Zumesscharakteristik. As used herein, a "desired die characteristic" refers to a cross-sectional area through the coolant passage that corresponds to or provides a desired coolant distribution or expected coolant distribution across the various coolant channels and / or outlets formed along the pressure-side slot sidewall 126 ,
    In some embodiments, a plug 138 may be used to reduce the flow cross-sectional area of the main channel outlets 133, as illustrated. The plug 138 may be configured to reduce, after its installation, the flow cross-sectional area through the cooling passage in which it is seated. In this case, the plug 138 is configured to allow a certain flow through the channel and direct the remaining fluid to alternative paths as desired. Here plugs of this type are referred to as "throttle plug". Accordingly, the throttle plug 138 may be configured to be inserted into the main channel outlet 133 and reduce its flow cross-sectional area by blocking a portion of the flow cross-sectional area of the outlet 133. The throttle plug 138 may be configured to reduce the flow area to a desired or predetermined flow area. In one embodiment, the throttle plug is provided with a central opening such that it has approximately a "floating tire" shape. The central opening is adapted to form a desired flow area at the outlet 133. As stated above, the predetermined flow area may relate to a desired coolant-impact characteristic and / or a desired Zumesscharakteristik, as the expert understands. The throttle plug 138 may be made of conventional materials and installed using conventional techniques (i.e., e.g., welding, brazing, etc.). Once installed, an outer surface of the throttle plug 138 may be flush with the surface of the pressure side slot side wall 126.
    The supply channel 134 may extend between the main channel 132 and the inner cooling channel 116 approximately in the circumferential direction. In a preferred embodiment, the feed channel 134 extends from the pressure-side slot sidewall 126 to the inner cooling passage 116 substantially circumferentially, and therebetween the feed passage 134 cuts through the main passage 132. It can be seen that the feed passage 134 provides a channel for a quantity of coolant. which flows away from the inner cooling passage 116 and the main passage 132. In some embodiments, the delivery channel 134 may include a delivery channel outlet 135 at the pressure-side slot sidewall 126. Similar to the main channel outlets 133, the feed channel outlet 135 may be configured to have a reduced flow cross-sectional area, i. a cross-sectional flow area or flow area reduced from the flow cross-sectional area of the feed channel 134. In addition, a throttle plug 138 can also be used to reduce the flow cross-sectional area of the feed channel outlet 135. The reduction of the flow cross-sectional area of the feed channel outlet 135 can be made for the same reasons as the main channel outlets 133. This means that the flow cross-sectional area can be reduced to achieve a desired coolant bounce characteristic, or the flow cross-sectional area can be reduced to provide a desired die characteristic is achieved.
    In a preferred embodiment, the feed channel outlet 135 may be configured to have an axial position on the pressure-side slot sidewall 126 that coincides with approximately the axial midpoint of the pressure side of the platform 110 as shown. In this case, upstream of the feed channel 134, i. With respect to the installation state of the turbine rotor blade 100 in a turbine axially upstream, a number of cooling holes 136 may be formed, and at least a number of cooling holes 136 may be located downstream of the feed channel 134, i. with respect to the installation state of the turbine rotor blade 100 in a turbine axially downstream. In a preferred embodiment, at least four cooling holes 136 are formed in front of the feed channel 134 and at least four cooling holes 136 are formed behind the feed channel 134. In one embodiment, the feed channel 134 is disposed approximately parallel to the leading edge 124 and trailing edge 121 of the platform 110.
    The cooling holes 136 may be formed so that each of the pressure-side slit side wall 126 extends to communicate with the main channel 132. The cooling holes 136 may extend from the pressure side slot side wall 126 to the main channel 132 with respect to the installed state of the turbine rotor blade 100 in a turbine approximately in the circumferential direction and be directed substantially parallel to the feed channel 134. The cooling aperture 136 may also be approximately parallel to the leading edge and trailing edge of the platform 110. The cooling holes 136 may be straight as shown. In a preferred embodiment, the cooling apertures 136 have smaller flow cross-sectional areas than the main channel 132 and / or the feed channel 134. It can be seen that the cooling apertures 136 may be configured so that in operation each aperture 136 directs a flow of coolant into a slot sidewall cavity extending between adjacent install rotor blades 100 is formed. The cooling holes 136 may be narrow so that the discharged coolant is expelled and directed against the slot side wall of the adjacent turbine blade 100 at a relatively high velocity, which generally increases the cooling efficiency of the coolant. It can be seen that the slot sidewall cavity and the slot sidewalls delimiting it are portions of the platform 110 that are difficult to cool and that the cooling aperture 136 formed in this manner provides effective cooling of that area. Although not shown, plugs 138 may be disposed in one or more of the cooling holes 136 to enhance the coolant distribution or impact characteristics when necessary. In one embodiment, the plugs 138 may completely occlude the coolant ports so that no coolant escapes through the slot sidewall.
    Referring now to Figure 10, there is illustrated an alternative embodiment of the present invention, platform cooling means 145. As shown, the supply passage 134 in this case extends from the suction side slot side wall 122 and not from the pressure side slot side wall 126. That is, the supply passage 134 extends from a suction-side slotted side wall 122 with respect to the installation state of the turbine rotor blade 100 in a turbine substantially circumferentially to a joint that communicates with the main passage 132, the supply passage 134 between the suction-side slash side wall 122 and the main channel 132 can intersect the inner cooling channel 116. In some embodiments, the supply passage 134 may include a plug 138 configured to substantially prevent coolant from escaping from the supply passage 134 along the suction-side slot sidewall 122. In this way, the main channel 132 can be connected to the inner cooling channel via a channel leading through the suction-side slot side wall 122, and the entire coolant flow flowing through the feed channel 134 can be directed into the main channel 132 where it contacts the various cooling holes 136 is distributed on the pressure side of the platform 110. More specifically, to achieve adequate coolant distribution across the various cooling holes 136, it may be necessary to prevent substantially all of the coolant from escaping through the opening formed in the suction side pressure surface 122. FIG. 10 reflects this in a configuration where the potential outlet is provided with a plug 138 which completely blocks it (referred to herein as a "plug"). In an alternative embodiment, the plug 138 for the feed channel 134 on the suction side 122 of the platform 110 may be a throttle plug, so that a desired amount of refrigerant is ejected at that location.
    In addition, the cooling holes 136, as illustrated in Fig. 10, may be formed curved. In one embodiment, the cooling apertures 136 form curved curves between the pressure-side slot sidewall 126 and the main channel 132. As can be seen, the curvature of the cooling aperture 136 increases the respective path between the main channel 132 and the pressure-side slot sidewall 126, increasing the inner platform surface over which the coolant deletes, thereby increasing the heat exchange between the coolant and the platform 110.
    The present invention also includes a novel method of forming internal cooling channels in the platform section of a rotor blade in a cost effective and efficient manner. Referring now to the flow chart 200 of FIG. 11, as the initial step 202, the main channel 132 may be formed in the pressure side of the platform 110. It will be appreciated that due to the relatively simple shape of the main channel 132, this can be made cost effective using conventional molding processes. Thus, as explained in greater detail below, the more expensive casting process otherwise used to form complicated shapes can be avoided.
    Once the main channel 132 is formed, in step 204, the supply channel 134 may be formed. Specifically, the feed channel 134 may be formed from an easily accessible location (e.g., either from the suction side slot sidewall 122 or the pressure side slot sidewall 126) using conventional line of sight milling or drilling processes. As step 206, the cooling holes 136 may similarly be formed using conventional line of sight milling or drilling processes. Again, the machining operation may originate from an accessible location (eg, the pressure-side slot sidewall 12S).
    If required, throttling or sealing plugs 138 may be manufactured in step 208. As discussed above, the throttle plugs 138 may have various different configurations and functions to restrict the flow area at an outlet. The plug 138 may be formed to completely close the flow area at the outlet. The throttle plugs 138 and plugs 138 may be made of conventional materials.
    Finally, the throttle plug 138 and / or the sealing plug 138 can be mounted in a step 210 at predetermined locations. This can be done using conventional methods such as welding, brazing or mechanical fastening.
    It can be seen that the main channel 132, the feed channel 134 and the cooling holes 136 in operation are adapted to lead coolant from the inner cooling channel 116 to a plurality of outlets formed on the pressure side slot side wall 126. More specifically, the platform cooling device according to the present invention removes a portion of the coolant from the cooling passage 116, uses the coolant to dissipate heat from the platform 110, and discharges the coolant into the slot sidewall cavity formed between adjacent rotor blades 100 so as to utilize the coolant will both cool the coolant cavity of adjacent blades 100 and reduce the suction of hot gas fluids. The present invention provides a mechanism for actively cooling the platform portion of a gas turbine rotor blade by efficiently forming a complex effective cooling assembly by utilizing a series of cost-saving conventional techniques. As stated, this area is typically difficult to cool, and given the mechanical stresses of this area, it is a location that is highly loaded, especially as the engine core temperatures are further increased. Accordingly, this type of active platform cooling is a significant key technology when higher firing temperatures, increased performance, and higher efficiency are desired. It can also be seen that the use of post-casting processing steps of platform cooling channel design provides greater flexibility in terms of redesign, reconfiguration or even retrofit platform cooling facilities. Finally, the present invention teaches the simplified cost-effective formation of platforms of cooling channels that provide complex geometries and effective platform coverage. Where hitherto complex geometries necessarily entail costly investment casting processes or the like, the present invention provides a teaching of methods by which cooling channels with complex shapes can be formed by abrading operations or simplified molding processes.
    A turbine rotor blade has a platform, a platform cooling device and a cooling channel 116 formed in it. The platform cooling device 130 further includes: a main channel 132 radially inward of the planar top surface relative to the installed state of the turbine rotor blade 100 in a turbine and moving from an axially downstream position within the pressure side and / or suction side of the platform axially upstream position, wherein the main channel 132 has a longitudinal axis which is aligned approximately parallel to the planar upper side; a supply passage 134 extending between the main passage 132 and the cooling passage 116; and a number of cooling holes 136, each cooling hole 136 extending away from the pressure side and / or suction side slot sidewalls 126, 122 to communicate with the main channel 132.
    LIST OF REFERENCE NUMBERS
    [0037]<Tb> 100 <September> turbine rotor blade<Tb> 102 <September> Sheet<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 <September> cooling channel<Tb> 117 <September> inlet<Tb> 119 <September> cavity<Tb> 120 <September> platform cooling channels<Tb> 121 <September> trailing edge<tb> 122 <SEP> Suction side edge or slot side wall<Tb> 124 <September> leading edge<tb> 126 <SEP> Print side edge or slot side wall<Tb> 130 <September> platform cooling device<Tb> 132 <September> main channel<Tb> 133 <September> Hauptkanalauslass<Tb> 134 <September> feed<Tb> 135 <September> delivery conduit<Tb> 136 <September> cooling holes<Tb> 138 <September> Plug<Tb> 145 <September> platform cooling device
    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 a blade (102) and a foot (104),a cooling passage (116) formed in the interior of the turbine rotor blade (100) extending in relation to the installed state of the turbine rotor blade (100) in a turbine from a connection with a coolant source on the foot (104) to at least the radial height of the platform (110) .the platform (110) having a planar, radially outwardly facing top (113) with respect to the installed state of the turbine rotor blade (100) in a turbine along a pressure side coincident with a pressure side (106) of the airfoil (102) with respect to the installation state of the turbine rotor blade (100) in a turbine extending from the airfoil (102) to a pressure-side slot side wall (126) in the circumferential direction, and along a suction side, which coincides with a suction side (105) of the airfoil (102), a planar, radially outwardly facing top (113) extending from the airfoil (102) circumferentially to a suction side slot sidewall (122),wherein the platform cooling device (130) comprises:a main passage (132) disposed radially inward with respect to the installed state of the turbine rotor blade (100) in a turbine relative to the planar top surface (113) and in the pressure side or the suction side of the platform (110) from an axially downstream position an axially upstream position, the main channel (132) having a longitudinal axis that is approximately parallel to the planar top surface (113),a supply passage (134) extending between the main passage (132) and the cooling passage (116), anda plurality of cooling holes 136, each cooling hole extending from the pressure-side or suction-side slot sidewall (122) to communication with the main channel (132).
    [2]
    2. A turbine rotor blade (100) according to claim 1, wherein:the main passage (132) extends in a turbine from an axially downstream position within the pressure side to an axially upstream position with respect to the installed state of the turbine rotor blade (100);wherein the main passage (132) is in a turbine from an axially downstream position on the pressure side gap surface (126) or adjacent to an axially upstream position on or adjacent to the pressure side slot side wall (126) in a turbine engine installed state Arc forms, wherein the arc of curvature of the shape of the profile of the pressure surface (106) of the airfoil (102) corresponds;wherein the main channel (132) has an axial length of at least 0.75 of the axial length of the airfoil (102) in a turbine with respect to the mounting state of the turbine rotor blade (100), the main channel (132) having a main channel outlet (133) at the axially downstream lying position of the pressure-side slit side wall (126) and another Hauptkanalauslass (133) at the axially upstream position on the pressure-side slot side wall (126), and wherein both the Hauptkanalauslass (133) at the axially upstream position and the Hauptkanalauslass (133 ) at the axially downstream position have a reduced flow cross-sectional area compared to the main channel (132).
    [3]
    The turbine rotor blade (100) of claim 2, wherein the main channel outlet (133) at the axially downstream position of the main channel (132) has a plug (138) defining the flow area restriction of the main channel outlet (133) at the axially downstream position.wherein the main channel outlet (133) at the upstream position of the main channel (132) comprises a plug (138) forming the flow area restriction of the main channel outlet (133) at the upstream position,wherein each of the two flow channel reduced main channel outlets (133) has a predetermined flow cross-sectional area to produce a specific coolant loading characteristic, such as a specific coolant exit velocity, and a specific coolant distribution across the cooling holes and / or outlets.
    [4]
    The turbine rotor blade (100) of claim 2, wherein the feed channel (134) extends circumferentially from the pressure side slot side wall (126) to the cooling passage (116) with respect to the installed state of the turbine rotor blade (100) in a turbine and interposes the main passage (132 ), wherein the supply channel (134) has a Zuführkanalauslass (135) on the pressure side slot side wall (126) andwherein the feed channel outlet (135) has a reduced flow cross-sectional area compared to the feed channel (134).
    [5]
    The turbine rotor blade (100) of claim 4, wherein the feed channel (134) at the pressure side slot sidewall (126) has a plug (138) forming (138) the cross sectional restriction at the feed channel outlet (135) which is reduced in the flow cross sectional area Feed duct outlet (135) has a predetermined cross-sectional area to produce a specific Kühlmittelbeaufschlagungscharakteristik, such as a specific coolant exit velocity, and a specific coolant distribution over the cooling holes and / or outlets.
    [6]
    The turbine rotor blade (100) of claim 4, wherein with respect to the installed state of the turbine rotor blade (100) in a turbine, the axial position of the supply channel outlet (135) on the pressure side slot side wall (126) comprises the axial center of the pressure side of the platform (110)at least a plurality of the cooling holes (136) are formed axially upstream of the feed channel (134) and at least a plurality of the cooling holes (136) are formed axially downstream of the feed channel (134);wherein a plurality of the cooling holes (136) have plugs (138).
    [7]
    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:Forming the main channel (132) within the pressure side of the platform (110),Machining the feed channel (134) along a predetermined straight path, wherein the straight path relative to the installed state of the turbine rotor blade (100) in a turbine has a beginning at an axially central location on the pressure side slot side wall (126) and extends circumferentially such that the supply channel (134) connects to the cooling channel (116) and intersects the main channel (132) therebetween, andMachining the plurality of cooling apertures (136) each having a beginning on the pressure-side slit sidewall (126) and extending substantially circumferentially for connection to the main channel (132).
    [8]
    8. The method of claim 7, wherein the main channel (132) is formed in a casting process,wherein the main channel (132) is configured to contact the main channel (132) with respect to the installed state of the turbine rotor blade (100) in a turbine from an axially downstream position on, or adjacent to, an axially upstream position on the pressure side slot sidewall (126) the pressure-side slot side wall (126) or forms an arc adjacent thereto, wherein the curvature of the arc corresponds to the contour of the pressure surface (106) of the airfoil (102), andwherein the cooling holes (136) are formed straight or curved.
    [9]
    The method of claim 8, wherein the main channel (132) is formed to connect a main channel outlet (133) at the axially downstream position to the pressure side slot sidewall (126) and another main channel outlet (133) at the axially upstream position the pressure-side slot side wall (126), andwherein both the main channel outlet (133) at the axially upstream position and the main channel outlet (133) at the axially downstream position have a reduced flow area compared to the main channel (133).
    [10]
    10. The method according to claim 9,wherein the feed channel (134) has a feed channel outlet (135) on the pressure side slot sidewall (126) andwherein the feed channel outlet (135) has a reduced flow cross-sectional area compared to the feed channel (135).
    [11]
    11. The method of claim 10, further comprising the steps of:Fabricating plugs (138) for each of the two main channel outlets (133) and the supply channel outlet (135) and attaching the plugs (138) for each of the two main channel outlets (133) and the delivery channel outlet (135), the plugs (138) defining the ones Set the flow cross-sectional area for the two main channel outlets (133) and the feed channel outlet (135).
    [12]
    12. The method of claim 11, wherein the two main channel outlets (133) and the Zufuhrkanalauslass (135) each have a predetermined cross-sectional flow area to produce a specific Kühlmittelbeaufschlagungscharakteristik, such as a specific coolant exit velocity, and a specific coolant distribution over the cooling holes and / or outlets ,
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    同族专利:
    公开号 | 公开日
    CN102444433B|2016-01-20|
    DE102011053930A1|2012-04-05|
    CN102444433A|2012-05-09|
    JP2012077745A|2012-04-19|
    JP5898898B2|2016-04-06|
    CH703894A2|2012-03-30|
    US8851846B2|2014-10-07|
    US20120082564A1|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 |
    2021-04-30| PL| Patent ceased|
    优先权:
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    US12/894,878|US8851846B2|2010-09-30|2010-09-30|Apparatus and methods for cooling platform regions of turbine rotor blades|
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