EP2574730A2 - Turbine Shroud Impingement System With Bellows - Google Patents
Turbine Shroud Impingement System With Bellows Download PDFInfo
- Publication number
- EP2574730A2 EP2574730A2 EP12186192A EP12186192A EP2574730A2 EP 2574730 A2 EP2574730 A2 EP 2574730A2 EP 12186192 A EP12186192 A EP 12186192A EP 12186192 A EP12186192 A EP 12186192A EP 2574730 A2 EP2574730 A2 EP 2574730A2
- Authority
- EP
- European Patent Office
- Prior art keywords
- impingement
- shroud
- bellows
- turbine shroud
- box
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Withdrawn
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
- F01D11/20—Actively adjusting tip-clearance
- F01D11/24—Actively adjusting tip-clearance by selectively cooling-heating stator or rotor components
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/11—Shroud seal segments
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/10—Two-dimensional
- F05D2250/18—Two-dimensional patterned
- F05D2250/183—Two-dimensional patterned zigzag
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
Definitions
- the present application and the resultant patent relate generally to gas turbine engines and more particularly relate to a turbine shroud impingement system with an impingement box in communication with a feed tube and a bellows for effective sealing, low leakage, and improved production.
- a gas turbine includes a number of turbine blades rotating in a hot gas pathway.
- This hot gas pathway may be enclosed and defined in part by a turbine shroud.
- a number of turbine shroud segments may be fixed in an annular array adjacent to the turbine blades. The turbine shroud thus protects an outer turbine casing and inhibits leakage of the hot combustion gases past the turbine blades without producing useful work therein.
- the turbine shroud defines the hot gas pathway in part, the turbine shroud may be cooled with a cooling air flow from the compressor or other source. This cooling air flow is required to maintain the structural integrity of the turbine shroud and maintain the clearances in the hot gas pathway. Because this cooling air flow is a parasitic loss on the overall gas turbine engine, reducing the leakage of such cooling air flow about the turbine shroud and elsewhere should promote overall gas turbine efficiency and performance.
- an improved turbine shroud cooling system Preferably, such an improved turbine shroud cooling system should provide a cooling air flow to the turbine shroud for sufficient cooling therein while limiting overall leakage losses and the like.
- the present invention resides in a turbine shroud impingement system.
- the turbine shroud impingement system may include a turbine shroud segment, an impingement box positioned within the turbine shroud segment, a feed tube in communication with the impingement box, and a bellows positioned about the feed tube.
- the present invention resides in a method of cooling a shroud segment.
- the method may include the steps of positioning an impingement box within the shroud segment, positioning a feed tube with a bellows within an inlet of the impingement box, maintaining the feed tube within the inlet of the impingement box by the axial compression of the bellows, and delivering a flow of air through the feed tube to the impingement box to cool the shroud segment.
- the present invention resides in a turbine shroud impingement system.
- the turbine shroud impingement system may include a turbine shroud segment, an impingement box with a number of impingement holes positioned within the turbine shroud segment, a feed tube in communication with the impingement box, and a bellows with a number of convolutions positioned about feed tube.
- Fig. 1 shows a schematic view of gas turbine engine 10 as may be used herein.
- the gas turbine engine 10 may include a compressor 15.
- the compressor 15 compresses an incoming flow of air 20.
- the compressor 15 delivers the compressed flow of air 20 to a combustor 25.
- the combustor 25 mixes the compressed flow of air 20 with a pressurized flow of fuel 30 and ignites the mixture to create a flow of combustion gases 35.
- the gas turbine engine 10 may include any number of combustors 25.
- the flow of combustion gases 35 is in turn delivered to a turbine 40.
- the flow of combustion gases 35 drives the turbine 40 so as to produce mechanical work.
- the mechanical work produced in the turbine 40 drives the compressor 15 via a shaft 45 and an external load 50 such as an electrical generator and the like.
- the gas turbine engine 10 may use natural gas, various types of syngas, and/or other types of fuels.
- the gas turbine engine 10 may be any one of a number of different gas turbine engines offered by General Electric Company of Schenectady, New York, including, but not limited to, those such as a 7 or a 9 series heavy duty gas turbine engine and the like.
- the gas turbine engine 10 may have different configurations and may use other types of components.
- Other types of gas turbine engines also may be used herein.
- Multiple gas turbine engines, other types of turbines, and other types of power generation equipment also may be used herein together.
- Fig. 2 shows a number of the components of the turbine 40. Specifically, a stage one bucket 55 and a stage two nozzle 60 are shown. The stage one bucket 55 may be surrounded by a stage one shroud 65. The stage one shroud 65 may be in communication with a flow of air 20 from the compressor 15 or other source.
- Known systems for delivering this flow of air 20 to the shroud 65 may include metered holes, spoolie systems, and the like. (Cooling systems are not limited to stage one use.) As described above, such known shroud cooling systems, however, may be subject to leakage therein.
- Fig. 3 shows a shroud 100 as may be described herein. Specifically, Fig. 3 shows a shroud segment 110. Any number of shroud segments 110 may be used in the overall shroud 100 in a circumferential array. As described above, the shroud segments 110 surround the buckets 55 and define the hot gas pathway therethrough. A lower surface 120 of the shroud segment 110 may face the buckets 55 and the flow of combustion gases 35 therein. Other components and other configurations may be used herein.
- Each shroud segment 110 may include a shroud impingement system 130 positioned therein.
- the shroud impingement system 130 may include an impingement box 140.
- a bottom surface 150 of impingement box 140 may have a number of impingement holes 160 therein.
- the impingement holes 160 may have any desired size, shape, or configuration. Any number of impingement holes 160 may be used herein.
- the impingement holes 160 face the lower surface 120 of the shroud segment 110 for cooling purposes.
- the impingement box 140 also may include an offset inlet 170.
- the offset inlet 170 may be positioned about a conical or an axial load face 180.
- the offset inlet 170 may have a substantial tube like shape 190.
- the offset inlet 170 may extend about the axial load face 180 into an interior 200 of the impingement box 140.
- Other components and other configurations may be used herein.
- the shroud impingement system 130 also may include a feed tube 220.
- the feed tube 220 may be in communication with the flow of air 20 from the compressor 15 or elsewhere and with the impingement box 140.
- the feed tube 220 may have any desired size, shape, or configuration.
- the shroud impingement system 130 also may include a bellows 230.
- the bellows 230 may be part of the feed tube 220.
- the bellows 230 may include a number of convolutions 240 and the like.
- the bellows 230 as a whole and the convolutions 240 may have any size, shape, or configuration.
- the bellows 230 acts as a type of expansion joint. Other types of deflection and sealing means may be used herein.
- the bellows 230 can withstand the internal pressure of the flow of air 20 within the feed tube 220 while also being flexible enough to accept axial, lateral, and/or angular deflections. Likewise, the bellows 230 may compensate for thermal movement, manufacturing and assembly variations, and the like.
- the configuration of the bellows 230 may vary with the configuration of the stages and the overall gas turbine engine and the output thereof.
- the feed tube 220 and the bellows 230 may be made out of any type of high temperature resistant materials and alloys. Other components and other configurations also may be used herein.
- the bellows 230 may be positioned between a first section 250 and a second section 260 of the feed tube 220 or otherwise.
- the second section 260 may have any type of geometry and may be sized to accommodate the offset inlet 170 of the impingement box 140.
- the second tube 260 may have an expanded spherical shape to accommodate the offset inlet 170.
- the feed tube 220 and the sections 250, 260 thereof may be sized with a predetermined diameter depending upon the desired flow rate of the flow of air 20 therein.
- the respective lengths of the sections 250, 260 and the bellows 230 may vary. Other components and other configurations also may be used herein.
- the shroud impingement system 130 may be positioned within an impingement box aperture 270 of the shroud segment 110.
- the impingement box aperture 270 may be sized and shaped to accommodate the intended impingement box 140. Standoffs tend to maintain a certain distance between the impingement box 140 and the shroud segment 110.
- the lower surface 120 of the shroud segment 110 may face the bottom surface 150 and the impingement holes 160 of the impingement box 140 for impingement cooling therein.
- a feed tube aperture 290 also may extend through the shroud segment 110.
- the feed tube aperture 290 may be sized and shaped to accommodate the feed tube 220 and the bellows 230 securely therein.
- Other components and other configurations also may be used herein.
- Fig. 4 shows an alternative embodiment of a shroud impingement system 300 as may be described herein.
- the bellows 230 may be attached directly to the offset inlet 170 of the impingement box 140 instead of the feed tube 220 described above.
- the bellow 230 extends directly to the first section 250 of the feed tube 220 without the use of the second section 260.
- a flange 310 and the like also may be attached to the bellows 230.
- Other components and other configurations also may be used herein.
- the feed tube 220 of the shroud impingement system 130 extends through the feed tube aperture 290 of the shroud segment 110.
- the second section 260 of the feed tube 220 may be positioned within the offset inlet 170 about the axial load face 180 of the impingement box 140.
- the connection between the feed tube 220 and the impingement box 140 may be maintained by the axial compression of the bellows 230.
- the bellows 230 thus reduces the leakage in the flow of air 20 by maintaining a sealing surface in spite of relative movement between the feed tube 220 and the impingement box 140.
- the sealing surface may be maintained regardless of slight relative movement therein. Additional sealing means also may be used herein.
- the shroud impingement system 130 thus delivers the flow of air 20 to the impingement box 140 so as to cool the lower surface 120 of the shroud segment 110 in an efficient manner.
- the bellows 230 may be attached to the offset inlet 170 of the impingement box 140 or elsewhere and may receive the feed tube 220 therein.
- the bellows 230 of the shroud impingement system 130 thus may reduce the need for tight machining tolerances that otherwise would be required for a rigid connection between the impingement box 140 and the feed tube 220.
- the bellows 230 therefore provides a constant sealing surface in a low cost, efficient sealing system with high reliability.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
- The present application and the resultant patent relate generally to gas turbine engines and more particularly relate to a turbine shroud impingement system with an impingement box in communication with a feed tube and a bellows for effective sealing, low leakage, and improved production.
- Generally described, a gas turbine includes a number of turbine blades rotating in a hot gas pathway. This hot gas pathway may be enclosed and defined in part by a turbine shroud. Specifically, a number of turbine shroud segments may be fixed in an annular array adjacent to the turbine blades. The turbine shroud thus protects an outer turbine casing and inhibits leakage of the hot combustion gases past the turbine blades without producing useful work therein.
- Because the turbine shroud defines the hot gas pathway in part, the turbine shroud may be cooled with a cooling air flow from the compressor or other source. This cooling air flow is required to maintain the structural integrity of the turbine shroud and maintain the clearances in the hot gas pathway. Because this cooling air flow is a parasitic loss on the overall gas turbine engine, reducing the leakage of such cooling air flow about the turbine shroud and elsewhere should promote overall gas turbine efficiency and performance.
- There is thus a desire for an improved turbine shroud cooling system. Preferably, such an improved turbine shroud cooling system should provide a cooling air flow to the turbine shroud for sufficient cooling therein while limiting overall leakage losses and the like.
- The present invention resides in a turbine shroud impingement system. The turbine shroud impingement system may include a turbine shroud segment, an impingement box positioned within the turbine shroud segment, a feed tube in communication with the impingement box, and a bellows positioned about the feed tube.
- The present invention resides in a method of cooling a shroud segment. The method may include the steps of positioning an impingement box within the shroud segment, positioning a feed tube with a bellows within an inlet of the impingement box, maintaining the feed tube within the inlet of the impingement box by the axial compression of the bellows, and delivering a flow of air through the feed tube to the impingement box to cool the shroud segment.
- The present invention resides in a turbine shroud impingement system. The turbine shroud impingement system may include a turbine shroud segment, an impingement box with a number of impingement holes positioned within the turbine shroud segment, a feed tube in communication with the impingement box, and a bellows with a number of convolutions positioned about feed tube.
- These and other features and improvements of the present application and the resultant patent will become apparent to one of ordinary skill in the art upon review of the following detailed description when taken in conjunction with the several drawings and the appended claims.
- Embodiments of the present invention will now be described, by way of example only, with reference to the accompanying drawings in which:
-
Fig. 1 is a schematic diagram of a gas turbine engine with a compressor, a combustor, and a turbine. -
Fig. 2 is a schematic diagram of portions of a number of stages of the turbine. -
Fig. 3 is a side view of a turbine shroud impingement system as may be described herein. -
Fig. 4 is a side view of an alternative embodiment of a turbine shroud impingement system as may be described herein. - Referring now to the drawings, in which like numerals refer to like elements throughout the several views,
Fig. 1 shows a schematic view ofgas turbine engine 10 as may be used herein. Thegas turbine engine 10 may include acompressor 15. Thecompressor 15 compresses an incoming flow ofair 20. Thecompressor 15 delivers the compressed flow ofair 20 to acombustor 25. Thecombustor 25 mixes the compressed flow ofair 20 with a pressurized flow offuel 30 and ignites the mixture to create a flow ofcombustion gases 35. Although only asingle combustor 25 is shown, thegas turbine engine 10 may include any number ofcombustors 25. The flow ofcombustion gases 35 is in turn delivered to aturbine 40. The flow ofcombustion gases 35 drives theturbine 40 so as to produce mechanical work. The mechanical work produced in theturbine 40 drives thecompressor 15 via ashaft 45 and anexternal load 50 such as an electrical generator and the like. - The
gas turbine engine 10 may use natural gas, various types of syngas, and/or other types of fuels. Thegas turbine engine 10 may be any one of a number of different gas turbine engines offered by General Electric Company of Schenectady, New York, including, but not limited to, those such as a 7 or a 9 series heavy duty gas turbine engine and the like. Thegas turbine engine 10 may have different configurations and may use other types of components. Other types of gas turbine engines also may be used herein. Multiple gas turbine engines, other types of turbines, and other types of power generation equipment also may be used herein together. -
Fig. 2 shows a number of the components of theturbine 40. Specifically, a stage one bucket 55 and a stage twonozzle 60 are shown. The stage one bucket 55 may be surrounded by a stage oneshroud 65. The stage oneshroud 65 may be in communication with a flow ofair 20 from thecompressor 15 or other source. Known systems for delivering this flow ofair 20 to theshroud 65 may include metered holes, spoolie systems, and the like. (Cooling systems are not limited to stage one use.) As described above, such known shroud cooling systems, however, may be subject to leakage therein. -
Fig. 3 shows ashroud 100 as may be described herein. Specifically,Fig. 3 shows ashroud segment 110. Any number ofshroud segments 110 may be used in theoverall shroud 100 in a circumferential array. As described above, theshroud segments 110 surround the buckets 55 and define the hot gas pathway therethrough. Alower surface 120 of theshroud segment 110 may face the buckets 55 and the flow ofcombustion gases 35 therein. Other components and other configurations may be used herein. - Each
shroud segment 110 may include ashroud impingement system 130 positioned therein. Theshroud impingement system 130 may include animpingement box 140. Abottom surface 150 ofimpingement box 140 may have a number ofimpingement holes 160 therein. Theimpingement holes 160 may have any desired size, shape, or configuration. Any number ofimpingement holes 160 may be used herein. Theimpingement holes 160 face thelower surface 120 of theshroud segment 110 for cooling purposes. Theimpingement box 140 also may include anoffset inlet 170. Theoffset inlet 170 may be positioned about a conical or anaxial load face 180. Theoffset inlet 170 may have a substantial tube likeshape 190. Theoffset inlet 170 may extend about theaxial load face 180 into aninterior 200 of theimpingement box 140. Other components and other configurations may be used herein. - The
shroud impingement system 130 also may include afeed tube 220. Thefeed tube 220 may be in communication with the flow ofair 20 from thecompressor 15 or elsewhere and with theimpingement box 140. Thefeed tube 220 may have any desired size, shape, or configuration. Theshroud impingement system 130 also may include a bellows 230. In this example, thebellows 230 may be part of thefeed tube 220. Thebellows 230 may include a number ofconvolutions 240 and the like. Thebellows 230 as a whole and theconvolutions 240 may have any size, shape, or configuration. Thebellows 230 acts as a type of expansion joint. Other types of deflection and sealing means may be used herein. Thebellows 230 can withstand the internal pressure of the flow ofair 20 within thefeed tube 220 while also being flexible enough to accept axial, lateral, and/or angular deflections. Likewise, thebellows 230 may compensate for thermal movement, manufacturing and assembly variations, and the like. The configuration of thebellows 230 may vary with the configuration of the stages and the overall gas turbine engine and the output thereof. Thefeed tube 220 and thebellows 230 may be made out of any type of high temperature resistant materials and alloys. Other components and other configurations also may be used herein. - The
bellows 230 may be positioned between afirst section 250 and asecond section 260 of thefeed tube 220 or otherwise. Thesecond section 260 may have any type of geometry and may be sized to accommodate the offsetinlet 170 of theimpingement box 140. For example, thesecond tube 260 may have an expanded spherical shape to accommodate the offsetinlet 170. Thefeed tube 220 and thesections air 20 therein. The respective lengths of thesections bellows 230 may vary. Other components and other configurations also may be used herein. - The
shroud impingement system 130 may be positioned within animpingement box aperture 270 of theshroud segment 110. Theimpingement box aperture 270 may be sized and shaped to accommodate the intendedimpingement box 140. Standoffs tend to maintain a certain distance between theimpingement box 140 and theshroud segment 110. Likewise, thelower surface 120 of theshroud segment 110 may face thebottom surface 150 and the impingement holes 160 of theimpingement box 140 for impingement cooling therein. Afeed tube aperture 290 also may extend through theshroud segment 110. Thefeed tube aperture 290 may be sized and shaped to accommodate thefeed tube 220 and thebellows 230 securely therein. Other components and other configurations also may be used herein. -
Fig. 4 shows an alternative embodiment of ashroud impingement system 300 as may be described herein. In this example, thebellows 230 may be attached directly to the offsetinlet 170 of theimpingement box 140 instead of thefeed tube 220 described above. Thebellow 230 extends directly to thefirst section 250 of thefeed tube 220 without the use of thesecond section 260. Aflange 310 and the like also may be attached to thebellows 230. Other components and other configurations also may be used herein. - In use, the
feed tube 220 of theshroud impingement system 130 extends through thefeed tube aperture 290 of theshroud segment 110. Thesecond section 260 of thefeed tube 220 may be positioned within the offsetinlet 170 about theaxial load face 180 of theimpingement box 140. The connection between thefeed tube 220 and theimpingement box 140 may be maintained by the axial compression of thebellows 230. Thebellows 230 thus reduces the leakage in the flow ofair 20 by maintaining a sealing surface in spite of relative movement between thefeed tube 220 and theimpingement box 140. The sealing surface may be maintained regardless of slight relative movement therein. Additional sealing means also may be used herein. Theshroud impingement system 130 thus delivers the flow ofair 20 to theimpingement box 140 so as to cool thelower surface 120 of theshroud segment 110 in an efficient manner. Alternatively, thebellows 230 may be attached to the offsetinlet 170 of theimpingement box 140 or elsewhere and may receive thefeed tube 220 therein. - The
bellows 230 of theshroud impingement system 130 thus may reduce the need for tight machining tolerances that otherwise would be required for a rigid connection between theimpingement box 140 and thefeed tube 220. Thebellows 230 therefore provides a constant sealing surface in a low cost, efficient sealing system with high reliability. - It should be apparent that the foregoing relates only to certain embodiments of the present application and the resultant patent. Numerous changes and modifications may be made herein by one of ordinary skill in the art without departing from the general spirit and scope of the invention as defined by the following claims and the equivalents thereof.
- Various aspects and embodiments of the present invention are defined by the following numbered clauses:
- 1. A turbine shroud impingement system, comprising:
- a turbine shroud segment;
- an impingement box with a plurality of impingement holes positioned within the turbine shroud segment;
- a feed tube in communication with the impingement box; and
- a bellows with a plurality of convolutions positioned about feed tube.
- 2. The turbine shroud impingement system of clause 1, wherein the shroud segment comprises a lower surface and wherein the impingement box comprises a bottom surface adjacent to the lower surface of the shroud segment.
- 3. The turbine shroud impingement system of clause 1, wherein the feed tube comprises a first section and a second section and wherein the bellows is positioned between the first section and the second section.
- 4. The turbine shroud impingement system of clause 1, wherein the bellows is attached to the impingement box.
Claims (14)
- A turbine shroud impingement system (130), comprising:a turbine shroud segment (110);an impingement box (140) positioned within the turbine shroud segment (110);a feed tube (220) in communication with the impingement box (14); anda bellows (230) positioned about feed tube (220).
- The turbine shroud impingement system (130) of claim 1, wherein the shroud segment (110) comprises a lower surface (120) and wherein the impingement box (140) comprises a bottom surface (150) adjacent to the lower surface (120) of the shroud segment (110).
- The turbine shroud impingement system (130) of claim 2, wherein the bottom surface (150) of the impingement box (140) comprises a plurality of impingement holes (160) therein.
- The turbine shroud impingement system (130) of any of claims 1 to 3, wherein the impingement box (140) comprises axial load face (1800 thereon.
- The turbine shroud impingement system (130) of claim 4, wherein the shroud segment (110) comprises a segment axial load face (280) and wherein the axial load face (180) of the impingement box (1400 is positioned about the segment axial load face (280).
- The turbine shroud impingement system (130) of claim 4 or 5, wherein the impingement box (140) comprises an offset inlet (170) positioned about the axial load face (180).
- The turbine shroud impingement system (130) of claim 6, wherein the offset inlet (170) comprises a tube-like shape (190).
- The turbine shroud impingement system (130) of any preceding claim, wherein the bellows (230) comprises a plurality of convolutions (240).
- The turbine shroud impingement system (130) of any preceding claim, wherein the feed tube (220) comprises a first section (250) and a second section (260) and wherein the bellows (230) is positioned between the first section (250) and the second section (260).
- The turbine shroud impingement system (130) of any preceding claim, wherein the bellows (230) is attached to the impingement box (140).
- The turbine shroud impingement system (130) of any preceding claim, wherein the shroud segment (110) comprises an impingement box aperture (270) therein.
- The turbine shroud impingement system (130) of any preceding claim, wherein the shroud segment (110) comprises a feed tube aperture (240) therein.
- The turbine shroud impingement system (130) of any preceding claim, further comprising a plurality of shroud segments (110).
- A method of cooling a shroud segment (110), comprising:positioning an impingement box (140) within the shroud segment (110);positioning a feed tube (220) with a bellows (230) within an inlet (170) of the impingement box (140);maintaining the feed tube (220) within the inlet (170) of the impingement box (140) by axial compression of the bellows (230); andflowing a flow of air (20) through the feed tube (220) to the impingement box (140) to cool the shroud segment (110).
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/249,554 US20130084160A1 (en) | 2011-09-30 | 2011-09-30 | Turbine Shroud Impingement System with Bellows |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2574730A2 true EP2574730A2 (en) | 2013-04-03 |
EP2574730A3 EP2574730A3 (en) | 2014-09-17 |
Family
ID=46963584
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP12186192.6A Withdrawn EP2574730A3 (en) | 2011-09-30 | 2012-09-26 | Turbine Shroud Impingement System With Bellows |
Country Status (3)
Country | Link |
---|---|
US (1) | US20130084160A1 (en) |
EP (1) | EP2574730A3 (en) |
CN (1) | CN103032114A (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP3214274A1 (en) * | 2016-02-26 | 2017-09-06 | General Electric Company | Encapsulated cooling for turbine shrouds |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US9915153B2 (en) | 2015-05-11 | 2018-03-13 | General Electric Company | Turbine shroud segment assembly with expansion joints |
Family Cites Families (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2540939A1 (en) * | 1983-02-10 | 1984-08-17 | Snecma | SEALING RING FOR A TURBINE ROTOR OF A TURBOMACHINE AND TURBOMACHINE INSTALLATION PROVIDED WITH SUCH RINGS |
US5273396A (en) * | 1992-06-22 | 1993-12-28 | General Electric Company | Arrangement for defining improved cooling airflow supply path through clearance control ring and shroud |
GB9725623D0 (en) * | 1997-12-03 | 2006-09-20 | Rolls Royce Plc | Improvements in or relating to a blade tip clearance system |
US6702550B2 (en) * | 2002-01-16 | 2004-03-09 | General Electric Company | Turbine shroud segment and shroud assembly |
US6997673B2 (en) * | 2003-12-11 | 2006-02-14 | Honeywell International, Inc. | Gas turbine high temperature turbine blade outer air seal assembly |
FR2883599B1 (en) * | 2005-03-23 | 2010-04-23 | Snecma Moteurs | CONNECTION DEVICE BETWEEN A COOLING AIR PASSING ENCLOSURE AND A DISTRIBUTOR'S TANK IN A TURBOMACHINE |
-
2011
- 2011-09-30 US US13/249,554 patent/US20130084160A1/en not_active Abandoned
-
2012
- 2012-09-26 EP EP12186192.6A patent/EP2574730A3/en not_active Withdrawn
- 2012-09-28 CN CN201210368092XA patent/CN103032114A/en active Pending
Non-Patent Citations (1)
Title |
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None |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP3214274A1 (en) * | 2016-02-26 | 2017-09-06 | General Electric Company | Encapsulated cooling for turbine shrouds |
Also Published As
Publication number | Publication date |
---|---|
EP2574730A3 (en) | 2014-09-17 |
US20130084160A1 (en) | 2013-04-04 |
CN103032114A (en) | 2013-04-10 |
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