Source: https://patents.google.com/patent/JP5898901B2/en
Timestamp: 2020-07-05 20:09:58
Document Index: 9126599

Matched Legal Cases: ['art 200', 'art 105', 'art 151', 'art 152', 'art 155', 'art 158', 'art 159', 'art 161']

JP5898901B2 - Apparatus and method for cooling the platform area of a turbine rotor blade - Google Patents
Apparatus and method for cooling the platform area of a turbine rotor blade Download PDF
JP5898901B2
JP5898901B2 JP2011213602A JP2011213602A JP5898901B2 JP 5898901 B2 JP5898901 B2 JP 5898901B2 JP 2011213602 A JP2011213602 A JP 2011213602A JP 2011213602 A JP2011213602 A JP 2011213602A JP 5898901 B2 JP5898901 B2 JP 5898901B2
JP2011213602A
JP2012077748A (en
スコット・エドモンド・エリス
ジョーン・ウェズリー・ハリス，ジュニア
エイドリアン・リオナル・スコット
2010-09-30 Priority to US12/894,993 priority Critical
2010-09-30 Priority to US12/894,993 priority patent/US8777568B2/en
2011-09-29 Application filed by ゼネラル・エレクトリック・カンパニイ filed Critical ゼネラル・エレクトリック・カンパニイ
2012-04-19 Publication of JP2012077748A publication Critical patent/JP2012077748A/en
2016-04-06 Publication of JP5898901B2 publication Critical patent/JP5898901B2/en
238000001816 cooling Methods 0.000 title claims description 114
239000002826 coolant Substances 0.000 claims description 68
238000003754 machining Methods 0.000 claims description 6
The present application relates generally to a combustion turbine engine that includes all types of combustion turbines as used in power generation and aircraft engines, as used herein and unless otherwise noted. Engine included. More specifically, but not exclusively, the present application relates to an apparatus, system, and / or method for cooling a platform region of a turbine rotor blade.
A gas turbine engine typically includes a compressor, a combustor, and a turbine. Compressors and turbines typically comprise multiple rows of airfoils or blades that are stacked in axial stages. Each stage typically comprises a row of circumferentially spaced and fixed stator blades and a set of rotor blades spaced circumferentially and rotating about a central axis or shaft. In operation, the compressor rotor blades rotate around the shaft to compress the air flow. The compressed air is then used in the combustor to burn the supplied fuel. The hot gas stream resulting from the combustion process expands through the turbine so that the rotor blades rotate the shaft on which the rotor blades are mounted. In this way, the energy contained in the fuel is converted to the mechanical energy of the rotating shaft, which can then be used, for example, to rotate a generator coil to generate electricity.
With reference to FIGS. 1 and 2, a turbine rotor blade 100 generally includes an airfoil portion or airfoil 102 and a blade root portion or blade root 104. The airfoil 102 can be represented as having a convex suction surface 105 and a concave pressure surface 106. Further, the airfoil 102 can be represented as having a leading edge 107 that is a front end and a trailing edge 108 that is a rear end. The blade root 104 includes a structure that secures the blade 100 to the rotor shaft (which structure typically includes a dovetail 109 as shown), a platform 110 from which the airfoil 102 extends, and a dovetail 109. And a shank 112 comprising a structure between the platform 110 and the platform 110.
As shown, the platform 110 can be substantially flat. More specifically, the platform 110 may have a flat upper surface 113, which may comprise a flat surface extending axially and circumferentially as shown in FIG. As shown in FIG. 2, the platform 110 may have a flat lower surface 114, which may also include a flat surface that extends axially and circumferentially. The top surface 113 and the bottom surface 114 of the platform 110 can be formed to be substantially parallel to each other. It will be appreciated that the platform 110 typically has a thin radial profile, ie, the radial distance between the top surface 113 and the bottom surface 114 of the platform 110 is relatively short, as shown.
In general, the platform 110 is used on the turbine rotor blade 100 to form the inner flow interface of the hot gas passage section of the gas turbine. The platform 110 further structurally supports the airfoil 102. During operation, the rotational speed of the turbine creates a mechanical load that creates a high stress region along the platform 110 that, when combined with high temperatures, eventually results in oxidation, creep, low frequency fatigue cracking, etc. Causes the formation of upper defects. These defects naturally adversely affect the useful life of the rotor blade 100. These harsh operating conditions, i.e. exposure of the hot gas path to extreme temperatures and mechanical loads associated with rotating blades, are fully functional and cost effective for manufacturing, are durable and have a long life It will be appreciated that significant challenges arise when designing a simple rotor blade platform 110.
One common solution to further improve the durability of the platform region 110 is to cool the platform region 110 with a stream of compressed air or other coolant during operation, and various platform designs of this type are known. It has been. However, those skilled in the art will appreciate that the platform region 110 presents several design issues that make it difficult to cool in this manner. In large part, this is due to the cumbersome shape of this region, i.e., as already mentioned, the platform 110 is a peripheral component that resides away from the central core of the rotor blade and is usually structurally sound. This is because it is designed to have a small radial thickness.
In order to circulate coolant, the rotor blade 100 typically includes one or more hollow internal coolings that penetrate at least the core of the blade 100 radially, including through the blade root 104 and the airfoil 102. A passage 116 (see FIGS. 3, 4, 5, and 7) is provided. As will be described in more detail below, to enhance heat exchange, the seed internal cooling passage 116 may have a serpentine path that bends through the central region of the blade 100, although other configurations are possible. Can be formed. In operation, coolant can flow into the central internal cooling passageway via one or more inlets 117 formed in the portion of the blade root 104 near the inner diameter. The coolant circulates through the blade 100 and passes through an outlet (not shown) formed in the airfoil and / or through one or more outlets (not shown) formed in the blade root 104. Can go out via. The coolant can be pressurized and can include, for example, pressurized air, pressurized air mixed with water, steam, and the like. In many cases, the coolant is compressed air diverted from the engine compressor, although other sources are possible. As will be described in more detail below, these internal cooling passages typically comprise a high pressure coolant region and a low pressure coolant region. The high pressure coolant region typically corresponds to the upstream portion of the internal cooling passage having a higher coolant pressure, and the low pressure coolant region corresponds to the downstream portion having a relatively low coolant pressure.
In some cases, coolant may be directed from the internal cooling passage 116 into a cavity 119 formed between the shank 112 and the platform 110 between adjacent rotor blades 100. From there, coolant can be used to cool the platform area 110 of the blade, and its conventional design is shown in FIG. This type of design typically draws air from one of the internal cooling passages 116 and uses that air to pressurize the cavity 119 formed between the shank 112 / platform 110. Once pressurized, this cavity 119 then supplies coolant to a cooling channel that extends through the platform 110. After passing through the platform 110, the cooling air can 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 design has several drawbacks. First, since the cooling circuit is formed only after two adjacent rotor blades 100 are assembled, the cooling circuit is partially not self-contained. This adds significant difficulty and complexity to mounting and flow inspection prior to mounting. A second drawback 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. Inadequate sealing may result in inadequate platform cooling and / or wasted cooling air. A third drawback is the inherent danger that gas in the hot gas path can be drawn into the cavity 119 or the platform 110 itself. This can occur when the cavity 119 is not maintained at a sufficiently high pressure during operation. If the pressure in the cavity 119 drops below the pressure in the hot gas passage, hot gas is drawn into the shank cavity 119, or the platform 110 itself, so that these components normally enter the hot gas passage condition. They are not designed to withstand the exposure of and thus are damaged.
4 and 5 show another type of conventional design for platform cooling. In this case, the cooling circuit is contained within the rotor blade 100 as shown and does not include the shank cavity 119. Cooling air is drawn from one of the internal cooling passages 116 that extend through the core of the blade 110 and back through the cooling channel 120 formed within the platform 110 (ie, the “platform cooling channel 120”). Led. As indicated by the arrows, the cooling air flows through the platform cooling channel 120 and exits the exit of the trailing edge 121 of the platform 110 or exits located along the suction side edge 122. . (When describing or referring to edges or surfaces of rectangular platform 110, each is based on its position relative to suction surface 105 and pressure surface 106 of airfoil 102 and / or blade 100 is mounted. Note that the rear engine is represented based on the forward and rearward direction of the rear engine, so that, as those skilled in the art will appreciate, the platform is configured with a trailing edge 121 as shown in FIGS. , Suction side edge 122, leading edge 124, and pressure side edge 126. Additionally, suction side edge 122 and pressure side edge 126 are also commonly referred to as "slash faces" and are adjacent rotor blades. The narrow cavities that form between 100 when they are installed are called "slash face cavities" A.)
It will be appreciated that the conventional designs of FIGS. 4 and 5 have advantages over the design of FIG. 3 in that they are not affected by changes in assembly or mounting conditions. However, conventional designs with this property have some limitations or drawbacks. First, as shown, only one circuit is provided on each side of the airfoil 102, thus limiting the control of the amount of cooling air used at various locations on the platform 110. There are drawbacks. Second, this type of conventional design is generally limited in scope. Although the serpentine path of FIG. 5 is improved over that of FIG. 4 in terms of coverage, there is still a dead area in the platform 110 that remains uncooled. Third, in order to achieve better coverage using a complexly formed platform cooling channel 120, the manufacturing cost is particularly high when the shape of the cooling channel requires a casting process to form. Increases dramatically. Fourth, these conventional designs typically dispose of the coolant in the hot gas path after use and before it is fully used, which adversely affects engine efficiency. Fifth, conventional designs with this characteristic generally have little flexibility. That is, the channel 120 is formed as an integral part of the platform 110 and there is little or no opportunity to change its function or configuration when operating conditions change. Moreover, these types of conventional designs are difficult to repair or retrofit.
U.S. Pat. No. 7,416,391
As a result, conventional platform cooling designs are inadequate in one or more critical areas. There remains a need for improved devices, systems, and methods that effectively and efficiently cool the platform area of turbine rotor blades, while also being cost effective, flexible in application, and durable in terms of manufacturing. ing.
Accordingly, the present application provides a platform cooling mechanism for a turbine rotor blade having a platform at an airfoil / blade root boundary, wherein the rotor blade is at least approximately from the connection of the blade root to a coolant source. An internal cooling passage formed in the rotor blade, extending to a radial height, wherein during operation the internal cooling passage comprises at least a high-pressure coolant region and a low-pressure coolant region, and the platform is closer to the inner diameter A platform cooling mechanism is provided, comprising a platform underside along the surface of the platform. The platform cooling mechanism includes a plate upper surface, the plate upper surface removably coupled to the platform lower surface, and a channel formed in the plate upper surface, the channel including an upstream end and a downstream end. When the plate is attached to the platform, the bottom surface of the platform forms a channel ceiling, and the upstream end of the channel is connected to the high-pressure coolant region of the internal cooling passage. There may be a high pressure connection to connect and a low pressure connection to connect the downstream end of the channel to the low pressure coolant region of the internal cooling passage.
The present application is a method of generating a platform cooling mechanism for a turbine rotor blade having a platform at an airfoil / blade root boundary, wherein the rotor blade is connected to a coolant source at the blade root from a connection of the platform. An internal cooling passage formed in the rotor blade, extending to at least approximately a radial height, wherein in operation, the internal cooling passage comprises at least a high pressure coolant region and a low pressure coolant region; A method of generating a platform cooling mechanism is further presented, comprising a platform underside along the inner diameter surface. The method includes machining a high pressure connection connecting the outlet to a high pressure coolant region of the internal cooling passage, the outlet being disposed at a first predetermined position near the inner diameter of the platform; Machining a low pressure connection connecting the inlet to the low pressure coolant region of the internal cooling passage, wherein the inlet is located at a second predetermined position near the inner diameter of the platform; Securing to the bottom surface of the platform, the plate comprising a channel formed on the top surface of the plate and having an upstream end and a downstream end, the channel opening through the top surface of the plate, thereby Attaching the plate to the platform, and the bottom surface of the platform constitutes the ceiling of the channel. Upstream end of the channel is connected to the outlet of the high-pressure connection, the downstream end of the channel is configured to be connected to the inlet of the low pressure connections, the channel comprises a tortuous channel.
These and other features of the present application will become apparent upon review of the following detailed description of the preferred embodiments, taken in conjunction with the drawings and the appended claims.
These and other features of the present invention will be more fully understood and appreciated by careful consideration of the following more detailed description of exemplary embodiments of the invention in conjunction with the accompanying drawings.
1 is a perspective view of an exemplary turbine rotor blade in which embodiments of the present invention may be used. FIG. FIG. 2 is a bottom view of a turbine rotor blade that may use embodiments of the present invention. 1 is a cross-sectional view of adjacent turbine rotor blades having a cooling system according to a conventional design. 1 is a top view of a turbine rotor blade having a platform with an internal cooling passage according to a conventional design. FIG. FIG. 6 is a top view of a turbine rotor blade having a platform with an internal cooling passage according to another conventional design. 2 is a perspective view of a plate having turbine rotor blades and serpentine cooling channels, according to an embodiment of the present application. FIG. It is a top view sectional view of a platform cooling mechanism by an embodiment of this application. FIG. 4 is a perspective view of a plate having serpentine cooling channels according to an embodiment of the present application. 1 is a cross-sectional side view of an unmodified conventional platform on which embodiments of the present application can be implemented. FIG. FIG. 10 is a cross-sectional side view of the platform of FIG. 9 showing how the platform can be modified to accept the exemplary plate embodiment of the present application. FIG. 10 is a side cross-sectional view of the platform of FIG. 9 showing the plate when it can be attached to the modified platform of FIG. 10 according to an exemplary embodiment of the present application. FIG. 6 is a perspective view of a plate having serpentine cooling channels according to an alternative embodiment of the present application. FIG. 13 is a cross-sectional side view of the platform showing the plate of FIG. 12 when it can be attached, according to an alternative embodiment of the present application. FIG. 4 is an exemplary method for generating a platform cooling mechanism according to an embodiment of the present application.
Turbine blades that are cooled by the internal circulation of coolant are typically radial, from the blade root through the platform region and into the airfoil, as described above in connection with some conventional cooling designs. It will be appreciated that an internal cooling passage 116 extending outwardly is provided. Some embodiments of the present invention can be used in conjunction with conventional coolant passages to enhance or enable effective, aggressive platform cooling, That is, it will be understood that it will be described in connection with an internal cooling passage 116 having a bent or serpentine configuration. As shown in FIGS. 6, 8, and 9, the meandering passage is usually configured to allow the coolant to flow in one direction and has a function of promoting heat exchange between the coolant and the surrounding rotor blade 100. In operation, pressurized coolant is supplied to the internal cooling passage 116 through a connection formed through the blade root 104, and the coolant is typically pressurized air extracted from the compressor. (Although other types of coolant such as steam may also be used in embodiments of the present invention). The pressure pumps the coolant through the internal cooling passage 116, which causes convection to transfer heat from the surrounding walls.
It will be appreciated that as the coolant travels through the internal cooling passage 116, the coolant loses pressure and the upstream portion of the internal cooling passage 116 has a higher pressure than the downstream portion of the coolant. . As will be described in more detail below, this pressure differential can be used to pump the coolant across or through an internal cooling passage formed in the platform. It will be appreciated that the present invention can be used with rotor blades 100 having various configurations of inner internal cooling passages and is not limited to internal cooling passages having a serpentine configuration. Thus, the term “internal cooling passage” as used in the present invention is intended to include any passage or hollow channel through which coolant can circulate through the rotor blades. As shown herein, the internal cooling passages 116 of the present invention extend at least to approximately the radial height of the platform 110 and have at least one relatively high coolant pressure region (hereinafter “high pressure region”). And in some cases may be an upstream portion within the serpentine passage) and at least one relatively low coolant pressure region (hereinafter referred to as the “low pressure region”), Which may be a downstream portion in the serpentine passage.
In general, various designs of the conventional inner internal cooling passage 116 are effective in creating positive cooling for an area within the rotor blade 100. However, as those skilled in the art will appreciate, the platform area has proven to be more problematic. This is due, at least in part, to the awkward shape of the platform, ie its narrow radial height, and the manner in which it is slightly away from the core or body of the rotor blade 100. However, the need for cooling of the platform is important considering the harsh temperature of the hot gas path and its exposure to high mechanical loads. As noted above, conventional platform cooling designs are not effective because they cannot address specific issues in this area, and their coolant utilization is inefficient and / or expensive to manufacture. .
6-14, several views of an exemplary embodiment of the present invention are shown. FIG. 6 shows a perspective view of a turbine rotor blade 100 and a plate 132 having serpentine cooling channels 133 according to an embodiment of the invention. As shown, the plate 132 can be attached to the platform 110. More specifically, the plate 132 can be attached to the platform lower surface 114. Similar to the top surface 113 of the platform 110, the platform bottom surface 114 may comprise a flat surface extending in the axial and circumferential directions. (Note that “flat” as used herein means a substantially or substantially planar shape. For example, the platform has a slightly curved and convex outer diameter surface. Those skilled in the art will appreciate that the curvature corresponds to the circumference of the turbine at the radial position of the rotor blades, and that the radius of curvature is flat on the platform. (As used herein, this type of platform shape is considered flat.) In this embodiment, a flat recess 131 is placed on the platform lower surface 114. Which is shown in FIGS. The flat recess 131 can be formed by one or more manufacturing methods such as, but not limited to, machining or casting. For example, existing rotor blades can be machined such that a suitable flat recess 131 is formed. In the present embodiment, the flat recess 131 can be located in the region of the platform lower surface 114 that substantially corresponds to the pressure side of the airfoil 102 of the blade 100. The flat recess 131 can be configured to receive a plate 132 according to the present invention.
As shown in FIGS. 8 and 12, the plate 132 may comprise a radially thin structure having a flat top surface 134 in which a channel 133 is formed. The flat upper surface 134 may extend axially and circumferentially when attached to the platform lower surface 114. In one embodiment, the channel 133 comprises a serpentine or bent path, although other configurations are possible. The channel 133 is formed on the surface of the plate 132 as shown, that is, it is not completely contained within the plate 132. Thus, the channel 133 can be represented as being left open through the top surface 134 of the plate. It will be appreciated that when the plate 132 is attached to the platform underside 114, the platform underside 114 thereby encloses the channel 133. That is, the platform lower surface 114 can form a ceiling 140 with respect to the channel 133 when the two surfaces merge.
The channel 133 can have an upstream end 138 and a downstream end 139. A high pressure connection 148 can connect the upstream end 138 of the channel 133 to the high pressure coolant region of the internal cooling passage 116. A low pressure connection 149 can connect the downstream end 139 of the channel 133 to the low pressure coolant region of the internal cooling passage 116. With respect to the longitudinal direction of the rotor blade 100, the upstream end 138 of the channel 133 may occupy a relatively forward position, and the downstream end 139 of the channel 133 may occupy a backward position.
As previously described, the airfoil 102 can be represented as having a pressure side 106 and a suction side 105, with the pressure side slash face 126 defining a platform edge corresponding to the pressure side 106 of the airfoil 102. obtain. In one embodiment, the plate 132 is disposed in the region of the platform lower surface 114 corresponding to the pressure side of the airfoil, as shown in FIG. Further, as shown in FIGS. 7, 8, and 12, in outline (ie, from the perspective of FIG. 7), the plate 132 may include a curved edge 151 and a straight edge 152. It will be appreciated that the curved edge 151 may substantially correspond in shape to the curved profile of the airfoil 102 where the pressure side 106 of the airfoil 102 is coupled to the platform 110. On the other hand, the shape of the straight edge 151 can substantially correspond to the straight outer shape of the pressure side slash face 126. More specifically, in some embodiments, the arrangement of curved edges 151 and straight edges 152 of plate 132 corresponds to the arrangement of the curved profile of airfoil 102 and the linear profile of pressure side slash face 126.
In some embodiments, the channel 133 is formed with a slash face portion 155. The slash face portion 155 may comprise a portion of the channel that lies in parallel and close to the straight edge 152 of the plate 132 (and thus when mounted, close to the pressure side slash face 126 as shown in FIG. 7). Is located). The upstream end of the slash face portion 155 can be proximate to the upstream end 138 of the channel 133. The length that the slash face portion 155 extends along the straight edge 152 of the plate 132 can be referred to as the “channel length of the slash face portion”. In a preferred embodiment, the channel length of the slash face portion may be at least 0.5 of the length of the slash face 126. More preferably, the channel length of the slash face portion may be longer than 0.75 of the length of the slash face 126. It will be appreciated that this placement of this portion of the channel provides several performance advantages. For example, because the slash face portion 155 is located near the upstream end 138 of the channel 133, the supply coolant must first flow in this region, so that this region becomes the downstream portion of the channel 133. You will receive a coolant with a lower temperature. Since this region is a platform region that receives some maximum operating temperature and is conventionally difficult to cool because it is away from the central region of the rotor blade 100, handling this region in this way is desirable cooling. It turns out that it is a policy.
Beyond the slash face portion, the channel 133 is provided with a turn 158 (ie, a sharp turning portion of approximately 180 °) that follows the turn 158 and enters the central region of the plate 132, which is the interior of the channel 133. Can be referred to as portion 159. The inner portion 159 may include a straight line portion downstream of the first turn-up portion 158 and a second turn-up portion 158 downstream thereof, the combination of which effectively makes the central region of the plate 132 an effective range. To do. The second folded portion 158 is located close to the downstream end 139 of the channel 133.
In some embodiments, the upstream end 138 of the channel 133 comprises an upstream plenum. Generally, the upstream plenum 138 includes a region with an increased channel width. As shown, in outline, the upstream plenum 138 may be substantially circular. The upstream plenum 138 forms a large space during operation where a plurality of coolant sources (if present) can be aggregated there and then introduced into the channel 133. The upstream plenum 138 also forms a larger target profile by which the connection to the high pressure connection 148 can be made. Similarly, in some embodiments, the downstream end 139 of the channel 133 comprises a downstream plenum. In general, the downstream plenum 139 also includes a region with an increased channel width, and as shown, the downstream plenum 139 can have a circular profile. The downstream plenum 139 forms a larger target profile by which the connection with the low pressure connection 149 can be made.
As described above, the high voltage connection 148 is connected to the upstream end 138 of the channel 133, and the low pressure connection 149 is connected to the downstream end 139 of the channel 133. This connection can be made using several configurations. For example, in one preferred embodiment (as shown in FIG. 8), the plate 132 includes an outer wall 144 that extends uninterrupted around its outer periphery. In this case, as shown in FIGS. 9 to 11, the connecting portions 148 and 149 may include a portion inside the blade 100 and a lower surface channel 161 formed in the platform 110. More specifically, the lower surface channel 161 includes a channel formed on the surface of the platform lower surface 114. It will be appreciated that, like channel 133, lower channel 161 remains open through the surface on which it is located, in this case, through platform lower surface 114. The lower channel 161 becomes encapsulated only after the plate 132 is attached to the platform 110. It will be appreciated that when the plate 132 is attached, the plate upper surface 134 can be represented as functioning as the floor 162 of the lower channel 161. As already mentioned, this configuration can be used for both the high pressure connection 148 and the low pressure connection 149. In the case of the high-voltage connection 148, the downstream ends of the lower surface channel 161 are shifted in the radial direction, but the position corresponds to the upstream end 138 of the channel 133. In the case of the low pressure connection portion 149, the upstream end portions of the lower surface channel 161 are shifted in the radial direction, but the position corresponds to the downstream end portion 139 of the channel 133.
In another embodiment, the outer wall 144 may include a sidewall inlet 165 and a sidewall outlet 166, each formed in the outer wall 144, as shown in FIG. In this case, the side wall inlet 165 can connect the upstream end 138 of the channel 133 directly through the outer wall 144 to the high pressure connection 148. The sidewall outlet 166 can also connect the downstream end 139 of the channel 133 directly through the outer wall 144 to the low pressure connection 149.
The plate 132 can be attached to the platform underside 114 using a variety of techniques. In some embodiments, the plate 132 is removably attached to the platform 110. As used herein, this type of attachment is intended to include any attachment that can be reasonably replaced so that plate 132 and / or blade 100 can be reused. This can include, for example, some types of welding, brazing, bonding, mechanical holding, and the like. As part of the step of attaching the plate, conventional steps can be used to seal the formed channel 133, and the connection made by the channel 133 with the connections 148, 149 results in a low voltage connection with the high voltage connection 148. A closed coolant circuit may be substantially generated between the portion 149. Thereby, substantially all of the coolant flowing from the high pressure connection 148 into the channel 133 is returned to the internal cooling passage 116 via the low pressure connection 149 for further use. One skilled in the art will appreciate that any sealing means may be used between the plate 132 and the platform lower surface 114. For example, a mechanical gasket, a chemical sealing material, etc. can be used.
Those skilled in the art will appreciate that the platform cooling mechanism 130 can be used to efficiently retrofit existing turbine rotor blades since the plate 132 and the platform 110 are not integrally formed components. Let's go. Further, the platform cooling mechanism 130 can take advantage of the existing internal cooling passages 116 of the turbine rotor blade 100, providing flexibility for adopting embodiments of the present invention on existing or new blades. . Plate 132 can also be adapted by post-cast changes. Various aspects of the plate 132 and channel 133 can be modified to optimize the cooling of the platform 110. Accordingly, the platform cooling mechanism 130 can be tailored to suit various turbine rotor blade configurations. Platform cooling mechanism 130 can be manufactured cost-effectively and efficiently because plate 132 can be manufactured independently of the various components of the turbine rotor blade. Further, the plate 132 can be pre-fabricated and later installed in the field.
FIG. 14 shows a flowchart 200 representing an exemplary method of generating a platform cooling mechanism 130 according to an embodiment of the present application. The flow diagram 200 may begin at step 202 where a flat recess 131 is machined into place on the platform lower surface 114 if desired. In some embodiments, the preferred location corresponds to the pressure side 126 of the airfoil 102. This machining process is illustrated in FIGS. FIG. 9 represents a cross section of the platform 110 before the recess 131 is formed. As shown, many existing platforms 110 have a flat lower surface 114, but some machine is needed to provide sufficient room for the plate 132 sized to obtain the desired cooling application area. Processing may be required. FIG. 10 shows areas that can be removed. The flat recess 131 may have an outer shape that substantially corresponds to the outer shape of the pressure side 106 of the airfoil 102 and may correspond to the outer shape of the plate 132 that is formed. It will be appreciated that in some cases, the flat recess 131 may pre-exist on the blade 100 as a casting work.
In step 204, a high pressure connection 148 and a low pressure connection 149 can be formed. The high pressure connection 148 in any case is such that it connects the high pressure coolant region of the internal cooling passage 116 to the final location of the upstream end 138 of the plate channel 133 or the side wall inlet 165 of the plate 132. Can have a predetermined configuration and position. In the absence of the sidewall inlet 165, the form of the high pressure connection 148 may comprise the form of the lower channel 161 as described above. Similarly, the low pressure connection 149 in any case is such that it connects the low pressure coolant region of the internal cooling passage 116 to the final location of the downstream end 139 of the plate channel 133 or the side wall outlet 166. Can have a predetermined configuration and position. In the absence of the sidewall outlet 166, as described above, the configuration of the low pressure connection 149 may comprise the configuration of the lower channel 161. The formation of the connections 148, 149 is a relatively inexpensive machine, especially considering the access to the relevant area of the blade 100 that is possible after the formation of the flat recess 131 and before the plate 132 is attached. It will be appreciated that processing steps can be used to complete.
In step 206, the plate 132 can be fabricated to the desired specifications. It will be appreciated that making the plate 132 independently simplifies the manufacturing process. For example, the channel 133 can be formed on the plate 132 by using a simple machining or casting process. On the other hand, forming the same channel in a monolithic platform will typically require a much more complex and expensive casting process.
In step 208, the plate 132 can be attached to the platform lower surface 114 so that the plate 132 fits inside the platform lower surface 114, thereby enclosing the channel 133 between the plate 132 and the platform lower surface 114. The plate 132 can be attached to the platform lower surface 114 so as to fit within the flat recess 131. Finally, in step 210, additional steps can be performed to seal the channel 133. As described above, the sealing of the channel 133 and the connection that the channel 133 makes with the connections 148, 149 result in a substantially closed coolant circuit between the high pressure connection 148 and the low pressure connection 149. obtain. The present invention enhances the seal created between the plate 132 and the platform underside 114, particularly when one or more underside channels 161 are used to connect the channel 133 to the coolant source. It will be appreciated that the centrifugal load generated during operation is utilized to achieve this.
As those skilled in the art will appreciate, the many different features and configurations described above with respect to some exemplary embodiments may be further selectively utilized to form other possible embodiments of the present invention. can do. For the sake of brevity and in view of the ability of those skilled in the art, all possible iterations will not be performed or described in detail, but all within the scope of the appended or different claims Combinations or possible embodiments are intended to be part of this application. Furthermore, from the above description of several exemplary embodiments of the invention, those skilled in the art will perceive improvements, changes and modifications. Such improvements, changes and modifications within the skill of the art are also intended to be covered by the appended claims. Furthermore, the matter described above pertains only to the embodiment described herein, and is described herein without departing from the spirit and scope of the present application as defined by the appended claims and their equivalents. It will be apparent that numerous changes and modifications can be made to the.
DESCRIPTION OF SYMBOLS 100 Turbine rotor blade 102 Aerofoil 104 Blade root part 105 Negative pressure surface 106 Positive pressure surface 107 Aerofoil front edge 108 Aerofoil rear edge 109 Dovetail 110 Platform 112 Shank 113 Platform upper surface 114 Platform lower surface 116 Internal cooling passage 117 Internal cooling passage inlet 119 Cavity 120 Platform cooling channel 121 Platform trailing edge 122 Platform suction side edge 124 Platform leading edge 126 Platform pressure side edge 130 Platform cooling mechanism 131 Flat recess 132 Plate 133 Meander cooling channel 134 Plate upper surface 138 Upstream end 139 Downstream end 140 Channel Ceiling 144 Outer wall 148 High pressure connection 149 Low pressure connection Part 151 Curved edge part 152 Straight edge part 155 Slash face part 158 Folding part 159 Inner part 161 Lower surface channel 162 Lower surface channel floor 165 Side wall inlet 166 Side wall outlet 200 Flow chart
A platform cooling mechanism (130) for a turbine rotor blade (100) having a platform (110) at the boundary between an airfoil (102) and a blade root (104), wherein the rotor blade (100) comprises the blade root ( 104), extending to the semi-radial height of at least the platform from a connection portion between the coolant supply source (110), an internal cooling passage formed in the rotor blade (100) (116) actuation among the internal cooling passage (116), at least, it includes a high pressure coolant region, and a low pressure coolant region, the platform (110) platform underside I along the inner side table surface thereof (114) cage, said platform cooling mechanism (130) is,
A plate (132) comprising a plate upper surface (134), the plate upper surface (134) being removably coupled to the platform lower surface (114);
A channel (133) formed on the plate upper surface (134), the channel (133) having an upstream end (138) and a downstream end (139), and penetrating the plate upper surface (134). Channel (133), wherein when the plate (132) is attached to the platform (110), the platform lower surface (114) constitutes the channel ceiling (140);
A high pressure connection (148) connecting the upstream end (138) of the channel (133) to the high pressure coolant region of the internal cooling passage (116);
A platform cooling mechanism (130) comprising a low pressure connection (149) connecting the downstream end (139) of the channel (133) to the low pressure coolant region of the internal cooling passage (116).
The plate (132) and the platform (110) are composed of components that are not integrally formed,
The platform (110) comprises a flat upper surface and a flat lower surface;
The internal cooling passage (116) comprises a serpentine internal cooling passage;
In use, the internal cooling passage (116) is configured to have a coolant flow direction, and with respect to the coolant flow direction, the high pressure coolant region comprises an upstream portion of the internal cooling passage (116); The low pressure coolant region comprises a downstream portion of the internal cooling passage (116);
The platform cooling mechanism (130) of any preceding claim.
The platform lower surface (114) comprises a flat surface extending axially and circumferentially;
The plate upper surface (134) comprises a flat surface extending axially and circumferentially;
The channel (133) formed in the plate upper surface (134) comprises a serpentine channel;
The airfoil (102) comprises a pressure side (106) and a suction side (105);
A pressure side slash face (126) comprises an edge of the platform (110) corresponding to the pressure side of the airfoil (102);
The plate (132) is disposed in a region of the platform lower surface (114) corresponding to the pressure side of the airfoil (102);
The upstream end (138) of the channel (133) occupies a front position and the downstream end (139) of the channel (133) occupies a rear position with respect to the front-rear direction of the rotor blade (100). ,
In profile, the plate (132) comprises a curved edge (151) and a straight edge (152), the curved edge (151) being connected to the airfoil (102) to the platform (110). The shape substantially corresponds to the curved outer shape of the airfoil (102) to be connected, and the linear edge (152) substantially corresponds to the linear shape of the pressure side slash face (126) in shape,
The arrangement of the curved edge (151) and the straight edge (152) of the plate (132) is relative to the arrangement of the curved outer shape of the airfoil (102) and the linear outer shape of the pressure side slash face (126). Are juxtaposed,
The channel (133) is provided with a slash face portion (155), and the slash face portion (155) is present in close proximity to and parallel to the straight edge (152) of the plate (132). The part of
The platform cooling mechanism (130) of claim 3.
The upstream end of the slash face portion (155) is proximate to the upstream end (138) of the channel (133);
The length at which the slash face portion (155) is in close proximity to and parallel to the linear edge (152) of the plate (132) constitutes the channel length of the slash face portion,
The channel length of the slash face portion is longer than 0.75 of the length of the pressure side slash face (126),
After passing the slash face portion (155), the channel (133) is in the central region of the plate (132) downstream of the first folded portion (158) and the first folded portion (158). An internal part (159) present,
The internal part (159) includes a straight part immediately downstream of the first folded part (158), and a second folded part (158) downstream of the linear part,
The second folded portion (158) is present proximate to the downstream end (139) of the channel (133);
The platform cooling mechanism (130) of claim 4.
The upstream end (138) of the channel (133) comprises an upstream plenum (138) with increased channel width;
The downstream end (139) of the channel (133) comprises a downstream plenum (139) with increased channel width;
The high pressure connection (148) is connected to the upstream plenum, and the low pressure connection (149) is connected to the downstream plenum;
The platform cooling mechanism (130) of claim 5.
The plate (132) comprises an outer wall (144), the outer wall (144) comprises a continuous wall extending seamlessly around the outer periphery of the plate (132);
The high voltage connection (148) includes a first lower surface channel (161) formed in the platform lower surface (114), and the first lower surface channel (161) penetrates the platform lower surface (114). When the plate (132) is attached to the platform lower surface (114), the plate upper surface (134) is in contact with the floor of the lower channel relative to at least a portion of the first lower channel (161). (162)
The low-pressure connection (149) includes a second lower surface channel (161) formed in the platform lower surface (114), and the second lower surface channel (161) penetrates the platform lower surface (114). When the plate (132) is attached to the platform (110), the upper surface (134) of the plate becomes lower with respect to at least a portion of the second lower surface channel (161). 162),
The downstream end of the first lower surface channel (161) at least partially overlaps the upstream end (138) of the channel (133) in the axial and circumferential directions, but in the radial direction. Slippage,
The upstream end of the second lower surface channel (161) at least partially overlaps the downstream end (139) of the channel (133) in the axial and circumferential directions, but in the radial direction. Is out of place,
The platform cooling mechanism (130) of claim 7.
A side wall inlet (165) and a side wall outlet (166), wherein the plate (132) comprises an outer wall (144), the outer wall (144) extending through the outer wall (144). Prepared,
The sidewall inlet (165) is configured to connect the upstream end (138) of the channel (133) to the high pressure connection (148);
The sidewall outlet (166) is configured to connect the downstream end (139) of the channel (133) to the low pressure connection (149);
What method der to produce a platform cooling mechanism (130) of a turbine rotor blade having a platform (110) at the boundary between the airfoil (102) the blade root portion (104) (100), said rotor blade (100) the blade root portion (104), extending to the semi-radial height of at least the platform from a connection portion between the coolant supply source (110), the inner formed in the rotor blade (100) in the cooling passage (116 ) comprises a, in operation, it said internal cooling passage (116), at least, a high pressure coolant region, and a low pressure coolant region, the platform (110) platform underside I along the inner side table surface thereof ( 114), the method comprising:
A step of machining high-pressure connection which connects the high pressure coolant region (148) of said internal cooling passage outlet (116), said outlet, said platform first predetermined inner side (110) A step arranged in a position;
A step of machining the low-pressure connection (149) connected to the low-pressure coolant region of the inlet interior cooling passage (116), said inlet, said platform (110) a second predetermined inner side of the A step arranged in a position;
Fixing the upper surface (134) of the plate (132) to the platform lower surface (114), wherein the plate (132) is formed on the plate upper surface (134), and has an upstream end (138) and a downstream end. A channel (133) comprising a portion (139), the channel (133) opening through the plate upper surface (134), thereby bringing the plate (132) into the platform (110). When mounted, the platform underside (114) comprises the ceiling (140) of the channel, and
The plate (132) is connected with the upstream end (138) of the channel (133) to the outlet of the high pressure connection (148), and the downstream end (139) of the channel (133) Configured to be connected to the inlet of the low pressure connection (149);
The channel (133) comprises a serpentine channel;
A method of generating a platform cooling mechanism (130).
In profile, the plate (132) comprises a curved edge (151) and a straight edge (152), the curved edge (151) being connected to the airfoil (102) to the platform (110). The shape substantially matches the curved outer shape of the airfoil (102) to be connected,
Machining a recess (131) having a flat ceiling on the platform lower surface (114) at a position substantially corresponding to the pressure side (106) of the airfoil (102), the flat ceiling A recess (131) having an outer shape corresponding to the outer shape of the plate (132);
Sealing the channel (133) such that substantially all coolant flowing through the channel (133) returns to the internal cooling passageway (116) during operation;
The plate (132) is attached to the platform lower surface (114) so that it fits within the recess (131) with the flat ceiling .
A method of generating a platform cooling mechanism (130) according to claim 10.
The channel (133) is provided with a slash face portion (155), and the slash face portion (155) is present in close proximity to and parallel to the straight edge (152) of the plate (132). The platform cooling mechanism (130) of claim 11, wherein the platform slash face portion (155) has an upstream end adjacent to the upstream end (138) of the channel (133). how to.
JP2011213602A 2010-09-30 2011-09-29 Apparatus and method for cooling the platform area of a turbine rotor blade Active JP5898901B2 (en)
US12/894,993 2010-09-30
US12/894,993 US8777568B2 (en) 2010-09-30 2010-09-30 Apparatus and methods for cooling platform regions of turbine rotor blades
JP2012077748A JP2012077748A (en) 2012-04-19
JP5898901B2 true JP5898901B2 (en) 2016-04-06
ID=45832658
JP2011213602A Active JP5898901B2 (en) 2010-09-30 2011-09-29 Apparatus and method for cooling the platform area of a turbine rotor blade
US (1) US8777568B2 (en)
JP (1) JP5898901B2 (en)
CN (1) CN102444429B (en)
CH (1) CH703877B1 (en)
DE (1) DE102011053874A1 (en)
EP3020920B1 (en) * 2014-11-12 2019-03-06 Ansaldo Energia IP UK Limited Cooling for turbine blade platform-aerofoil joints
EP3250789A1 (en) * 2015-01-28 2017-12-06 Siemens Energy, Inc. Turbine airfoil cooling system with integrated airfoil and platform cooling
US10605099B2 (en) * 2015-07-31 2020-03-31 General Electric Company Cooling arrangements in turbine blades
US10030537B2 (en) 2015-10-12 2018-07-24 General Electric Company Turbine nozzle with inner band and outer band cooling
US10385727B2 (en) 2015-10-12 2019-08-20 General Electric Company Turbine nozzle with cooling channel coolant distribution plenum
US9995172B2 (en) 2015-10-12 2018-06-12 General Electric Company Turbine nozzle with cooling channel coolant discharge plenum
US10443437B2 (en) 2016-11-03 2019-10-15 General Electric Company Interwoven near surface cooled channels for cooled structures
US10519782B2 (en) * 2017-06-04 2019-12-31 United Technologies Corporation Airfoil having serpentine core resupply flow control
US10323520B2 (en) 2017-06-13 2019-06-18 General Electric Company Platform cooling arrangement in a turbine rotor blade
GB1605297A (en) 1977-05-05 1988-06-08 Rolls Royce Nozzle guide vane structure for a gas turbine engine
FR2758855B1 (en) * 1997-01-30 1999-02-26 Snecma Ventilation system for mobile vane platforms
JP3411775B2 (en) 1997-03-10 2003-06-03 三菱重工業株式会社 Gas turbine blade
CA2262064C (en) 1998-02-23 2002-09-03 Mitsubishi Heavy Industries, Ltd. Gas turbine moving blade platform
JP2000220404A (en) * 1999-01-28 2000-08-08 Toshiba Corp Gas turbine cooling blade
JP3421271B2 (en) 1999-03-01 2003-06-30 株式会社キャットアイ Engagement device
AT483098T (en) 1999-09-24 2010-10-15 Gen Electric Guestburn bucket with pruned cooled platform
FR2810365B1 (en) * 2000-06-15 2002-10-11 Snecma Moteurs System for ventilation of a pair of juxtaposed dawn platforms
EP1566519A1 (en) 2004-02-23 2005-08-24 Siemens Aktiengesellschaft High temperature resisting component for a fluidic machine and fluidic machine using this component.
WO2006029983A1 (en) * 2004-09-16 2006-03-23 Alstom Technology Ltd Turbine engine vane with fluid cooled shroud
JP2006188962A (en) * 2004-12-28 2006-07-20 Mitsubishi Heavy Ind Ltd Cooling structure of gas turbine high temperature part
US7513738B2 (en) * 2006-02-15 2009-04-07 General Electric Company Methods and apparatus for cooling gas turbine rotor blades
US7416391B2 (en) * 2006-02-24 2008-08-26 General Electric Company Bucket platform cooling circuit and method
US7575416B2 (en) * 2006-05-18 2009-08-18 United Technologies Corporation Rotor assembly for a rotary machine
JP5281245B2 (en) * 2007-02-21 2013-09-04 三菱重工業株式会社 Gas turbine rotor platform cooling structure
US8262357B2 (en) * 2009-05-15 2012-09-11 Siemens Energy, Inc. Extended length holes for tip film and tip floor cooling
2010-09-30 US US12/894,993 patent/US8777568B2/en active Active
2011-09-22 DE DE201110053874 patent/DE102011053874A1/en active Pending
2011-09-27 CH CH01593/11A patent/CH703877B1/en unknown
2011-09-28 CN CN201110305898.XA patent/CN102444429B/en active IP Right Grant
2011-09-29 JP JP2011213602A patent/JP5898901B2/en active Active
CN102444429A (en) 2012-05-09
CH703877B1 (en) 2016-01-15
US8777568B2 (en) 2014-07-15
DE102011053874A1 (en) 2012-04-05
JP2012077748A (en) 2012-04-19
US20120082549A1 (en) 2012-04-05
CH703877A2 (en) 2012-03-30
CN102444429B (en) 2015-04-08
US9845694B2 (en) 2017-12-19 Flow directing cover for engine component
US8876463B2 (en) 2014-11-04 Interturbine vane with multiple air chambers
JP5879022B2 (en) 2016-03-08 Turbine blade cooling circuit
JP5931351B2 (en) 2016-06-08 Turbine vane
JP2017115862A (en) 2017-06-29 Fillet optimization for turbine airfoil
CN102444431B (en) 2015-11-25 For the apparatus and method of cooling turbine rotor blade platform area
US10619491B2 (en) 2020-04-14 Turbine airfoil with trailing edge cooling circuit
CN103184895B (en) 2016-03-16 Turbine rotor blade platform cooling unit
JP2017115878A (en) 2017-06-29 Cooling circuit for multi-wall blade
JP2007327493A (en) 2007-12-20 Serpentine cooling circuit and method for cooling shroud
EP1956192A2 (en) 2008-08-13 Gas turbine engine component cooling scheme
Ref document number: 5898901