WO2017077850A1 - ガスタービンエンジンの抽気構造 - Google Patents
ガスタービンエンジンの抽気構造 Download PDFInfo
- Publication number
- WO2017077850A1 WO2017077850A1 PCT/JP2016/080778 JP2016080778W WO2017077850A1 WO 2017077850 A1 WO2017077850 A1 WO 2017077850A1 JP 2016080778 W JP2016080778 W JP 2016080778W WO 2017077850 A1 WO2017077850 A1 WO 2017077850A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- partition member
- turbine
- bleed
- engine
- chamber
- Prior art date
Links
- 230000000740 bleeding effect Effects 0.000 title abstract description 4
- 238000004891 communication Methods 0.000 claims abstract description 22
- 238000011144 upstream manufacturing Methods 0.000 claims abstract description 9
- 238000005192 partition Methods 0.000 claims description 71
- 238000000605 extraction Methods 0.000 claims description 39
- 238000000638 solvent extraction Methods 0.000 abstract 2
- 239000007789 gas Substances 0.000 description 47
- 230000002093 peripheral effect Effects 0.000 description 16
- 238000002485 combustion reaction Methods 0.000 description 7
- 239000000567 combustion gas Substances 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 238000003780 insertion Methods 0.000 description 2
- 230000037431 insertion Effects 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 238000007792 addition Methods 0.000 description 1
- 239000000809 air pollutant Substances 0.000 description 1
- 231100001243 air pollutant Toxicity 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 238000012217 deletion Methods 0.000 description 1
- 230000037430 deletion Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
Images
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
- F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
- F02C6/06—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas
- F02C6/08—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas the gas being bled from the gas-turbine compressor
-
- 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
- F01D17/00—Regulating or controlling by varying flow
-
- 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
- F01D17/00—Regulating or controlling by varying flow
- F01D17/10—Final actuators
- F01D17/105—Final actuators by passing part of the fluid
-
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/14—Casings modified therefor
-
- 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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
-
- 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
- F01D9/00—Stators
- F01D9/06—Fluid supply conduits to nozzles or the like
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
- F02C7/16—Cooling of plants characterised by cooling medium
- F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/16—Control of working fluid flow
- F02C9/18—Control of working fluid flow by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages
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- 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
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
-
- 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
- F05D2240/12—Fluid guiding means, e.g. vanes
-
- 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
- F05D2240/14—Casings or housings protecting or supporting assemblies within
-
- 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
- F05D2260/60—Fluid transfer
- F05D2260/605—Venting into the ambient atmosphere or the like
-
- 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
- F05D2270/00—Control
- F05D2270/01—Purpose of the control system
- F05D2270/08—Purpose of the control system to produce clean exhaust gases
- F05D2270/082—Purpose of the control system to produce clean exhaust gases with as little NOx as possible
Definitions
- the present invention relates to a structure for extracting gas compressed by a compressor of a gas turbine engine to the outside of the engine.
- the object of the present invention is to stably suppress the gas drift in the engine while avoiding the enlargement of the entire engine by utilizing the space and components in the gas turbine engine.
- An object of the present invention is to provide a gas turbine engine bleed structure capable of ensuring proper combustion.
- an extraction structure is a structure for extracting compressed gas from a chamber that receives compressed gas from a compressor and supplies the compressed gas to a combustor in a gas turbine engine.
- a turbine casing that covers an outer periphery of a turbine of a turbine engine; an engine housing that surrounds the turbine casing and forms an extraction space communicating with the chamber between the turbine casing; and the extraction housing provided in the engine housing,
- An extraction duct for deriving compressed gas in the space to the outside of the engine housing; and an annular partition member that is disposed upstream of the extraction duct in the extraction space and partitions the extraction space from the chamber.
- a plurality of communication holes for communicating the upstream side and the downstream side of the partition member.
- the compressed gas in the chamber collides with the partition member and flows in the circumferential direction, the compressed gas is extracted downstream from the plurality of communication holes of the partition member. Therefore, the compressed air from the compressor toward the combustor is prevented from flowing in a circumferential direction. Moreover, since such an effect can be obtained by providing a partition member that divides the extraction space from the chamber, the circumferential direction of the compressed gas in the engine during extraction is avoided while avoiding an increase in the size of the entire gas turbine engine. The drift is suppressed, and stable combustion can be ensured in the combustor.
- the partition member includes a trunk portion extending in a radial direction in a longitudinal sectional view along the axial direction, and a diameter of the trunk portion. It has an outer-diameter side leg part and an inner-diameter side leg part respectively extending in the axial direction from both ends in the direction, and the plurality of communication holes may be formed in the body part. Furthermore, a plurality of slits in the axial direction may be formed in at least one of the outer diameter side leg portion and the inner diameter side leg portion of the partition member. According to this configuration, the partition member can have radial elasticity by a simple structure, and the compressed gas can be effectively prevented from leaking to the downstream side from the portion other than the communication hole of the partition member.
- the partition member may be attached to a turbine support member that supports a turbine on the engine housing. According to this configuration, it is possible to suppress an increase in the number of components such as the support member by providing the partition member by effectively using the existing components of the gas turbine engine.
- FIG. 1 is a side view in which a part of a gas turbine engine (hereinafter simply referred to as a gas turbine) GE having an extraction structure according to an embodiment of the present invention is broken.
- the gas turbine GE compresses the air A introduced from the outside with the compressor 1 and guides it to the combustor 3.
- the fuel F is burned together with the compressed air CA in the combustor 3, and the obtained high-temperature and high-pressure combustion gas G is used.
- the turbine 5 is driven.
- a plurality of can-type combustors 3 are arranged at equal intervals along the circumferential direction of the gas turbine GE.
- the compressor 1 side in the direction of the axis C of the gas turbine GE may be referred to as “front” and the turbine 5 side may be referred to as “rear”.
- “Before” and “after” attached to the names of elements constituting the embodiment have the same meaning.
- “axial direction”, “circumferential direction”, and “radial direction” mean the axial C direction, circumferential direction, and radial direction of the gas turbine GE, unless otherwise specified.
- an axial flow type compressor is used as the compressor 1.
- the compressed air CA compressed by the axial flow type compressor 1 passes through the diffuser 9 connected to the downstream end of the compressor 1 and then flows into the chamber 11.
- the chamber 11 is a space formed around the combustor 3 that communicates with the compressor outlet via the diffuser 9.
- the chamber 11 receives the compressed air CA from the compressor 1 and supplies the compressed air CA to the combustor 3.
- the high-temperature and high-pressure combustion gas G generated in the combustor 3 flows into the turbine 5.
- the combustion gas G that has driven the turbine 5 is discharged to the outside of the gas turbine GE through an exhaust passage 15 connected downstream (backward) of the turbine 5.
- the turbine 5 includes a large number of stationary blades 19 and a large number of moving blades 23 arranged on the outer peripheral surface of a rotor 21 that constitutes a rotating portion of the gas turbine GE.
- the outer periphery of the stationary blade 19 and the moving blade 23 after the first-stage stationary blade 19 (hereinafter sometimes referred to as “first-stage stationary blade 19A”) at the front end that forms the inlet of the turbine 5, that is, the turbine 5
- the outer periphery is covered with a turbine casing 25.
- a turbine casing 25 that covers the outer periphery of the turbine 5 is connected and fixed to the inside of the engine housing 17, and each stationary blade 19 is attached to the turbine casing 25.
- a turbine casing 25 is surrounded by an engine housing 17 that is a housing of the entire gas turbine GE.
- a portion of the engine housing 17 located outside the turbine 5 is referred to as a turbine housing portion 31.
- the inner peripheral wall surface 31a of the turbine housing portion 31 is formed as a flat cylindrical surface extending substantially parallel to the axial direction.
- the turbine casing 25 has a connecting flange portion 35 projecting radially outward from its front end.
- the front end portion 19Aa of the first stage stationary blade 19A is positioned on the connecting flange portion 35 in the circumferential direction and the radial direction.
- the first stage stationary blade 19 ⁇ / b> A is positioned in the axial direction by a support ring 41 fixed to a flange (not shown) provided on the inner peripheral surface of the engine housing 17 and a connecting flange portion 35.
- the turbine casing 25 has a shape that increases in diameter toward the rear, and has a rear end flange 45 that protrudes radially outward at the rearmost end of the rear end portion.
- the turbine casing 25 is supported by the rear end portion 31 b of the turbine housing portion 31 of the engine housing 17 through the rear end flange 45.
- Each stationary blade 19 is supported by the turbine casing 25 by engaging with an engagement mechanism provided on the inner peripheral portion of the turbine casing 25.
- the structure in which the turbine casing 25 supports the stationary blade 19 of the turbine 5 is not limited to the example described above.
- An extraction space 51 communicating with the chamber 11 is formed between the turbine housing portion 31 of the engine housing 17 and the turbine casing 25 inside thereof.
- the extraction space 51 forms an extraction path for extracting compressed air CA from the chamber 11 in the gas turbine GE.
- the turbine housing portion 31 of the engine housing 17 is provided with an extraction duct 53 that guides the air in the extraction space 51 to the outside of the engine housing 17.
- the bleed duct 53 is provided only at one place in the circumferential direction of the turbine housing portion 31.
- the bleed duct 53 is provided in the axial direction position corresponding to the third stage stationary blade 19 of the turbine housing portion 31, but the axial direction position of the bleed duct 53 is not limited to this example. .
- the extraction space 51 is partitioned from the chamber 11 by an annular partition member 55 disposed in front of the extraction duct 53 in a space between the turbine housing portion 31 of the engine housing 17 and the turbine casing 25 inside thereof. Yes. That is, the partition member 55 is disposed on the upstream side of the bleed duct 53 in the bleed passage for extracting the compressed air CA from the chamber 11.
- the partition member 55 divides the chamber 11 and the extraction space 51 in the axial direction, and the compressed air CA is led out to the extraction duct 53 from the extraction space 51 on the downstream side (rear side) of the partition member 55.
- the partition member 55 in the present embodiment in a longitudinal sectional view along the axial direction, extends in the axial direction from the radially extending body 61 and from both radial ends of the trunk 61. It has an outer diameter side leg portion 63 and an inner diameter side leg portion 65.
- the partition member 55 is U-shaped (when the outer diameter side leg portion 63 and the inner diameter side leg portion 65 are equal in length) or J shape (outer diameter) in a longitudinal sectional view along the axial direction.
- the side legs 63 and the inner diameter side legs 65 are different in length).
- the partition member 55 is formed by bending a metal plate-like member, and both end portions in the radial direction of the body portion 61 are curved rearward.
- the partition member 55 by providing the outer diameter side leg portion 63 and the inner diameter side leg portion 65 having the above-described structure, the partition member 55 has elasticity in the radial direction.
- the partition member 55 is formed with a plurality of communication holes 67 that allow the upstream side and the downstream side of the partition member 55 to communicate with each other.
- the plurality of communication holes 67 are formed in the body portion 61.
- each communication hole 67 is formed as a circular hole, but the shape of the communication hole 67 is not limited to a circular shape.
- the plurality of communication holes 67 are arranged at equal intervals in the circumferential direction.
- the outer diameter side leg 63 and the inner diameter side leg 65 of the partition member 55 each have a plurality of slits 69 that are cuts in the axial direction.
- the same number of slits 69 as the communication holes 67 are formed in the outer diameter side leg portion 63 at equal intervals in the circumferential direction.
- each slit 69 extends to the communication hole 67 of the body portion 61 and opens to each communication hole 67.
- one slit 69 is formed at each circumferential position between the adjacent slits 69 and 69 of the outer diameter side leg portion 63.
- the slit 69 may be omitted, by forming the slit 69 in at least one leg of the outer diameter side leg 63 and the inner diameter side leg 65 of the partition member 55, the elasticity of the partition member 55 in the radial direction can be increased. Can be bigger.
- the slit 69 is formed in both the outer diameter side leg portion 63 and the inner diameter side leg portion 65, but the slit 69 is formed only in one of the outer diameter side leg portion 63 and the inner diameter side leg portion 65 of the partition member 55. May be formed.
- the number and arrangement of the slits 69 are not limited to the illustrated example, and may be set as appropriate.
- the partition member 55 By giving the partition member 55 elasticity in the radial direction, the compressed air CA is prevented from leaking to the downstream side from portions other than the communication hole 67 of the partition member 55, and the circumferential flow of the compressed air CA is reliably suppressed. can do.
- the inner diameter side portion (inner diameter side leg portion 65 in this embodiment) of the partition member 55 is disposed on the outer peripheral portion of the turbine 5 that becomes high temperature, large thermal expansion occurs. Even in such an environment, the partition member 55 has elasticity, so that the partition member 55 is in contact with the engine housing 17 and the turbine casing 25.
- the structure that gives the partition member 55 elasticity in the radial direction is not limited to the above example.
- the outer diameter side leg portion 63 of the partition member 55 is in contact with the engine housing 17, and the inner diameter side leg portion 65 is in contact with the turbine casing 25 which is a turbine support member. Further, the body portion 61 of the partition member 55 is detachably fastened to the connection flange portion 35 of the turbine casing 25.
- annular housing fitting surface portion 71 protruding inward in the radial direction is provided on the inner peripheral surface of the turbine housing portion 31 of the engine housing 17.
- the inner peripheral surface of the housing fitting surface portion 71 is formed substantially parallel to the axial direction in a longitudinal sectional view.
- annular outer diameter side fitting surface portion 73 protruding outward in the radial direction is provided on the outer peripheral surface of the outer diameter side leg portion 63 of the partition member 55.
- the outer peripheral surface of the outer diameter side fitting surface portion 73 is formed substantially parallel to the axial direction in a longitudinal sectional view.
- annular turbine casing fitting surface portion 75 protruding outward in the radial direction is provided.
- the outer peripheral surface of the turbine casing fitting surface portion 75 is formed substantially parallel to the axial direction in a longitudinal sectional view.
- annular inner diameter side fitting surface portion 77 protruding radially inward is provided on the inner peripheral surface of the inner diameter side fitting surface portion 77 .
- the inner peripheral surface of the inner diameter side fitting surface portion 77 is formed substantially parallel to the axial direction in a longitudinal sectional view.
- fitting surface portions 71 to 77 provided in each of these members may be omitted, by providing the fitting surface portions 71 to 77, the partition member 55, the engine housing 17 and the turbine casing 25 can be separated. It is more reliably prevented that a gap is generated in the fitting portion.
- the body portion 61 of the partition member 55 is formed with insertion holes 79 through which connecting members are inserted at a plurality of locations in the circumferential direction. As shown in FIG. 5, the body portion 61 of the partition member 55 is inserted at a plurality of locations in the circumferential direction with connecting members such as bolts B3 through the insertion holes 79 of the body portion 61, and the connection flange portions 35 of the turbine casing 25. Are attached to the turbine casing 25.
- the support structure of the member 55 is not limited to this. For example, as shown by a two-dot chain line in FIG.
- the partition member 55 ⁇ / b> A is arranged slightly rearward, and a flange (on the outer peripheral surface of the portion (or the rear portion thereof) covering the first stage blade 23 of the turbine casing 25) It is good also as a structure which supports the partition member 55 to the turbine casing 25 by providing the flange 61 and fastening the trunk
- the part supported by the turbine support member in the partition member 55 includes the trunk portion 61, stable support is possible.
- the partition member 55 is not necessarily supported via the trunk portion 61. Absent.
- the partition member 55 may be supported only via the inner diameter side leg portion 65.
- partition member 55 is attached to the turbine casing 25 functioning as a turbine support member that supports the turbine 5 to the engine housing 17, existing components of the gas turbine GE are effectively used. By doing, the increase in the number of parts by providing the partition member 55 can be suppressed.
- the compressed air CA in the chamber 11 shown in FIG. 2 collides with the partition member 55 and flows in the circumferential direction, and then the plurality of communication holes of the partition member 55. 67 flows into the extraction space 51 formed on the downstream side of the partition member 55.
- circumferential drift of the compressed air CA in the chamber 11 is suppressed, and the velocity distribution is made uniform. Therefore, the compressed air CA from the compressor 1 toward the combustor 3 is prevented from flowing in the circumferential direction.
- Compressed air CA in the extraction space 51 is extracted from the extraction space 51 through the extraction duct 53 to the outside of the gas turbine GE.
- the partition member 55 having the above-described configuration, the uneven flow of the compressed air CA in the gas turbine GE is effectively suppressed without providing a plurality of extraction ducts at equal intervals in the circumferential direction.
- an example in which only one bleed duct 53 is provided in the engine housing 17 to suppress an increase in size of the entire gas turbine engine is shown.
- the number of extraction ducts provided in the engine housing 17 is not limited to one.
- the plurality of communication holes 67 are arranged at equal intervals in the circumferential direction in the partition member 55, but may not necessarily be arranged at equal intervals.
- the interval between the communication holes 67 is large in the circumferential region in the vicinity of the bleed duct 53, and the interval between the communication holes 67 is small in the circumferential region further away from the bleed duct 53. You may arrange in.
- the opening area of the some communicating hole 67 of a partition member is made the same, you may vary an opening area by the communicating hole 67.
- the opening area of the communication hole 67 may be small in the circumferential region near the extraction duct 53, and the opening area of the communication hole 67 may be increased in the circumferential region farther from the extraction duct 53. By comprising in this way, the drift of the circumferential direction of compressed air CA in the upstream of the partition member 51 is suppressed more effectively.
- the gas turbine engine using air as a working gas has been described as an example of the gas turbine engine to which the extraction structure is applied.
- a working gas other than air such as methane gas. There may be.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Control Of Turbines (AREA)
Abstract
Description
3 燃焼器
5 タービン
11 チャンバ
17 エンジンハウジング
25 タービンケーシング
51 抽気空間
53 抽気ダクト
55 仕切り部材
67 連通孔
69 スリット
CA 圧縮空気(圧縮ガス)
GE ガスタービンエンジン
Claims (4)
- ガスタービンエンジンにおいて、圧縮機からの圧縮ガスを受け入れて燃焼器へ供給するチャンバから圧縮ガスを抽気する構造であって、
前記ガスタービンエンジンのタービンの外周を覆うタービンケーシングと、
前記タービンケーシングを囲繞し、このタービンケーシングとの間に前記チャンバに連通する抽気空間を形成するエンジンハウジングと、
前記エンジンハウジングに設けられて、前記抽気空間内の圧縮ガスを前記エンジンハウジングの外部へ導出する抽気ダクトと、
前記抽気空間における、前記抽気ダクトよりも上流側に配置されて前記抽気空間を前記チャンバから区画する環状の仕切り部材であって、この仕切り部材の上流側と下流側とを連通させる複数の連通孔を有する仕切り部材と、
を備える抽気構造。 - 請求項1に記載の抽気構造において、前記仕切り部材は、軸心方向に沿った縦断面視で、径方向に延びる胴部と、この胴部の径方向両端からそれぞれ軸心方向に延びる外径側脚部および内径側脚部とを有し、前記胴部に前記複数の連通孔が形成されている抽気構造。
- 請求項2に記載の抽気構造において、前記仕切り部材の前記外径側脚部および内径側脚部の少なくとも一方に、軸心方向に延びる複数のスリットが形成されている抽気構造。
- 請求項1から3のいずれか一項に記載の抽気構造において、前記仕切り部材が、前記タービンを前記エンジンハウジングに支持するタービン支持部材に取り付けられている抽気構造。
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE112016005111.5T DE112016005111B8 (de) | 2015-11-05 | 2016-10-18 | Entlüftungsstruktur für einen Gasturbinenmotor |
CN201680064473.5A CN108350748B (zh) | 2015-11-05 | 2016-10-18 | 燃气涡轮发动机的抽气结构 |
GB1809082.9A GB2560468B (en) | 2015-11-05 | 2016-10-18 | Bleeding structure for gas turbine engine |
US15/969,425 US10975767B2 (en) | 2015-11-05 | 2018-05-02 | Bleeding structure for gas turbine engine |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2015217813A JP6563312B2 (ja) | 2015-11-05 | 2015-11-05 | ガスタービンエンジンの抽気構造 |
JP2015-217813 | 2015-11-05 |
Related Child Applications (1)
Application Number | Title | Priority Date | Filing Date |
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US15/969,425 Continuation US10975767B2 (en) | 2015-11-05 | 2018-05-02 | Bleeding structure for gas turbine engine |
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WO2017077850A1 true WO2017077850A1 (ja) | 2017-05-11 |
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PCT/JP2016/080778 WO2017077850A1 (ja) | 2015-11-05 | 2016-10-18 | ガスタービンエンジンの抽気構造 |
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US (1) | US10975767B2 (ja) |
JP (1) | JP6563312B2 (ja) |
CN (1) | CN108350748B (ja) |
DE (1) | DE112016005111B8 (ja) |
GB (1) | GB2560468B (ja) |
WO (1) | WO2017077850A1 (ja) |
Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPH1026353A (ja) * | 1996-07-12 | 1998-01-27 | Mitsubishi Heavy Ind Ltd | ガスタービン燃焼器のバイパス空気量制御装置 |
JP2004076726A (ja) * | 2002-08-15 | 2004-03-11 | General Electric Co <Ge> | 圧縮機の抽気ケース |
JP2005171795A (ja) * | 2003-12-09 | 2005-06-30 | Mitsubishi Heavy Ind Ltd | ガスタービン燃焼装置 |
JP2010059850A (ja) * | 2008-09-03 | 2010-03-18 | Mitsubishi Heavy Ind Ltd | ガスタービン |
JP2013520613A (ja) * | 2010-02-25 | 2013-06-06 | ゼネラル・エレクトリック・カンパニイ | タービンシュラウド支持熱シールド |
JP2013531159A (ja) * | 2010-03-18 | 2013-08-01 | ゼネラル・エレクトリック・カンパニイ | デブリフィルタを備えたタービンシュラウドハンガー |
Family Cites Families (55)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3520635A (en) * | 1968-11-04 | 1970-07-14 | Avco Corp | Turbomachine shroud assembly |
FR2280791A1 (fr) * | 1974-07-31 | 1976-02-27 | Snecma | Perfectionnements au reglage du jeu entre les aubes et le stator d'une turbine |
JPS5554636A (en) * | 1978-10-16 | 1980-04-22 | Hitachi Ltd | Combustor of gas turbine |
US4413470A (en) * | 1981-03-05 | 1983-11-08 | Electric Power Research Institute, Inc. | Catalytic combustion system for a stationary combustion turbine having a transition duct mounted catalytic element |
US5160241A (en) * | 1991-09-09 | 1992-11-03 | General Electric Company | Multi-port air channeling assembly |
US5363641A (en) * | 1993-08-06 | 1994-11-15 | United Technologies Corporation | Integrated auxiliary power system |
US5611197A (en) * | 1995-10-23 | 1997-03-18 | General Electric Company | Closed-circuit air cooled turbine |
FR2750451B1 (fr) * | 1996-06-27 | 1998-08-07 | Snecma | Dispositif de soufflage de gaz de reglage de jeux dans une turbomachine |
US6065282A (en) * | 1997-10-29 | 2000-05-23 | Mitsubishi Heavy Industries, Ltd. | System for cooling blades in a gas turbine |
US6227800B1 (en) * | 1998-11-24 | 2001-05-08 | General Electric Company | Bay cooled turbine casing |
JP2001107748A (ja) | 1999-10-07 | 2001-04-17 | Toshiba Corp | ガスタービンプラント |
DE10027833A1 (de) * | 2000-06-05 | 2001-12-13 | Alstom Power Nv | Verfahren zum Kühlen einer Gasturbinenanlage sowie Gasturbinenanlage zur Durchführung des Verfahrens |
US20020157400A1 (en) * | 2001-04-27 | 2002-10-31 | Siemens Aktiengesellschaft | Gas turbine with combined can-type and annular combustor and method of operating a gas turbine |
EP1446556B1 (de) * | 2001-10-30 | 2006-03-29 | Alstom Technology Ltd | Turbomaschine |
US7124590B2 (en) * | 2003-10-03 | 2006-10-24 | United Technologies Corporation | Ejector for cooling air supply pressure optimization |
FR2871398B1 (fr) * | 2004-06-15 | 2006-09-29 | Snecma Moteurs Sa | Procede de fabrication d'un carter de stator de turbine |
JP4476116B2 (ja) * | 2004-12-27 | 2010-06-09 | 三菱重工業株式会社 | ガスタービン |
US7770375B2 (en) * | 2006-02-09 | 2010-08-10 | United Technologies Corporation | Particle collector for gas turbine engine |
US7785063B2 (en) * | 2006-12-15 | 2010-08-31 | Siemens Energy, Inc. | Tip clearance control |
JP2009156542A (ja) * | 2007-12-27 | 2009-07-16 | Mitsubishi Heavy Ind Ltd | ガスタービンの燃焼器 |
EP2078837A1 (de) * | 2008-01-11 | 2009-07-15 | Siemens Aktiengesellschaft | Zapfluftentnahmevorrichtung für einen Verdichter eines Gasturbinentriebwerks |
FR2931872B1 (fr) * | 2008-05-28 | 2010-08-20 | Snecma | Turbine haute pression d'une turbomachine avec montage ameliore du boitier de pilotage des jeux radiaux d'aubes mobiles. |
ES2370949T3 (es) | 2008-07-16 | 2011-12-26 | Siemens Aktiengesellschaft | Válvula controlada por fluído para una turbina de gas y para una cámara de combustión. |
US8147192B2 (en) * | 2008-09-19 | 2012-04-03 | General Electric Company | Dual stage turbine shroud |
KR101366584B1 (ko) * | 2008-10-08 | 2014-02-24 | 미츠비시 쥬고교 가부시키가이샤 | 가스 터빈 및 그 운전 방법 |
WO2010084573A1 (ja) * | 2009-01-20 | 2010-07-29 | 三菱重工業株式会社 | ガスタービン設備 |
GB0908373D0 (en) * | 2009-05-15 | 2009-06-24 | Rolls Royce Plc | Fluid flow control device |
US8342798B2 (en) * | 2009-07-28 | 2013-01-01 | General Electric Company | System and method for clearance control in a rotary machine |
JP5192507B2 (ja) * | 2010-03-19 | 2013-05-08 | 川崎重工業株式会社 | ガスタービンエンジン |
JP4841680B2 (ja) * | 2010-05-10 | 2011-12-21 | 川崎重工業株式会社 | ガスタービン圧縮機の抽気構造 |
FR2961867B1 (fr) | 2010-06-24 | 2014-06-13 | Snecma | Prelevement d'air a travers le diffuseur d'un compresseur centrifuge d'une turbomachine |
US8448444B2 (en) * | 2011-02-18 | 2013-05-28 | General Electric Company | Method and apparatus for mounting transition piece in combustor |
US9151182B2 (en) * | 2011-04-22 | 2015-10-06 | General Electric Company | System and method for removing heat from a turbomachine |
EP2581583B1 (en) * | 2011-10-14 | 2016-11-30 | General Electric Technology GmbH | Method for operating a gas turbine and gas turbine |
US9316111B2 (en) * | 2011-12-15 | 2016-04-19 | Pratt & Whitney Canada Corp. | Active turbine tip clearance control system |
EP2634381A1 (de) * | 2012-02-28 | 2013-09-04 | Siemens Aktiengesellschaft | Gasturbine mit einem Abgas-Diffusor und Stützrippen |
US9115595B2 (en) * | 2012-04-09 | 2015-08-25 | General Electric Company | Clearance control system for a gas turbine |
WO2014185997A2 (en) * | 2013-02-04 | 2014-11-20 | United Technologies Corporation | Rotary valve for bleed flow path |
US9376961B2 (en) * | 2013-03-18 | 2016-06-28 | General Electric Company | System for controlling a flow rate of a compressed working fluid to a combustor fuel injector |
CN104420887B (zh) * | 2013-08-30 | 2016-06-15 | 哈尔滨汽轮机厂有限责任公司 | 一种燃气轮机的透平机 |
DE112014004335B4 (de) * | 2013-09-20 | 2022-09-22 | Mitsubishi Heavy Industries, Ltd. | Gasturbine, Gasturbinen-Steuergerät und Gasturbinen-Betriebsverfahren |
GB201317757D0 (en) * | 2013-10-08 | 2013-11-20 | Rolls Royce Plc | A method of manufacturing an article by hot pressing and ultrasonically inspecting the article |
JP2015217813A (ja) | 2014-05-19 | 2015-12-07 | 株式会社東海理化電機製作所 | 操作入力装置 |
US10018360B2 (en) * | 2014-06-06 | 2018-07-10 | United Technologies Corporation | Turbine stage cooling |
US9803487B2 (en) * | 2014-06-26 | 2017-10-31 | Siemens Energy, Inc. | Converging flow joint insert system at an intersection between adjacent transitions extending between a combustor and a turbine assembly in a gas turbine engine |
EP2987965A1 (de) * | 2014-08-21 | 2016-02-24 | Siemens Aktiengesellschaft | Gasturbine mit Ringkanal und Verteilrohr in diesem |
US10100738B2 (en) | 2015-01-20 | 2018-10-16 | United Technologies Corporation | Overcooled air cooling system with annular mixing passage |
EP3325779A1 (en) * | 2015-07-20 | 2018-05-30 | Siemens Energy, Inc. | Gas turbine seal arrangement |
CN108291452B (zh) * | 2015-11-26 | 2020-10-30 | 三菱日立电力系统株式会社 | 燃气轮机及燃气轮机的部件温度调节方法 |
US20170306846A1 (en) * | 2016-04-22 | 2017-10-26 | General Electric Company | Ventilation system for turbomachine using bladeless airflow amplifier |
US20170350265A1 (en) * | 2016-06-01 | 2017-12-07 | United Technologies Corporation | Flow metering and directing ring seal |
US10309246B2 (en) * | 2016-06-07 | 2019-06-04 | General Electric Company | Passive clearance control system for gas turbomachine |
US10427075B2 (en) * | 2017-06-20 | 2019-10-01 | United Technologies Corporation | Debris strainer for gas turbine engine cooling flow |
FR3082872B1 (fr) * | 2018-06-25 | 2021-06-04 | Safran Aircraft Engines | Dispositif de refroidissement d'un carter de turbomachine |
US10584613B2 (en) * | 2018-07-18 | 2020-03-10 | United Technologies Corporation | Necked debris separator for a gas turbine engine |
-
2015
- 2015-11-05 JP JP2015217813A patent/JP6563312B2/ja active Active
-
2016
- 2016-10-18 DE DE112016005111.5T patent/DE112016005111B8/de active Active
- 2016-10-18 CN CN201680064473.5A patent/CN108350748B/zh active Active
- 2016-10-18 GB GB1809082.9A patent/GB2560468B/en active Active
- 2016-10-18 WO PCT/JP2016/080778 patent/WO2017077850A1/ja active Application Filing
-
2018
- 2018-05-02 US US15/969,425 patent/US10975767B2/en active Active
Patent Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPH1026353A (ja) * | 1996-07-12 | 1998-01-27 | Mitsubishi Heavy Ind Ltd | ガスタービン燃焼器のバイパス空気量制御装置 |
JP2004076726A (ja) * | 2002-08-15 | 2004-03-11 | General Electric Co <Ge> | 圧縮機の抽気ケース |
JP2005171795A (ja) * | 2003-12-09 | 2005-06-30 | Mitsubishi Heavy Ind Ltd | ガスタービン燃焼装置 |
JP2010059850A (ja) * | 2008-09-03 | 2010-03-18 | Mitsubishi Heavy Ind Ltd | ガスタービン |
JP2013520613A (ja) * | 2010-02-25 | 2013-06-06 | ゼネラル・エレクトリック・カンパニイ | タービンシュラウド支持熱シールド |
JP2013531159A (ja) * | 2010-03-18 | 2013-08-01 | ゼネラル・エレクトリック・カンパニイ | デブリフィルタを備えたタービンシュラウドハンガー |
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JP2017089436A (ja) | 2017-05-25 |
US10975767B2 (en) | 2021-04-13 |
US20180252159A1 (en) | 2018-09-06 |
CN108350748A (zh) | 2018-07-31 |
DE112016005111T5 (de) | 2018-08-02 |
GB2560468A8 (en) | 2018-10-17 |
DE112016005111B8 (de) | 2022-12-15 |
GB201809082D0 (en) | 2018-07-18 |
DE112016005111B4 (de) | 2022-10-06 |
GB2560468B (en) | 2020-10-14 |
CN108350748B (zh) | 2020-05-19 |
GB2560468A (en) | 2018-09-12 |
JP6563312B2 (ja) | 2019-08-21 |
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