WO2017159397A1 - 多段軸流圧縮機及びガスタービン - Google Patents
多段軸流圧縮機及びガスタービン Download PDFInfo
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- WO2017159397A1 WO2017159397A1 PCT/JP2017/008438 JP2017008438W WO2017159397A1 WO 2017159397 A1 WO2017159397 A1 WO 2017159397A1 JP 2017008438 W JP2017008438 W JP 2017008438W WO 2017159397 A1 WO2017159397 A1 WO 2017159397A1
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- Prior art keywords
- port
- rotation axis
- bleed
- port part
- rotating shaft
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- 239000012530 fluid Substances 0.000 claims abstract description 86
- 230000002093 peripheral effect Effects 0.000 claims abstract description 33
- 238000000605 extraction Methods 0.000 claims description 151
- 238000005452 bending Methods 0.000 claims description 63
- 239000007789 gas Substances 0.000 claims description 17
- 239000000567 combustion gas Substances 0.000 claims description 6
- NCGICGYLBXGBGN-UHFFFAOYSA-N 3-morpholin-4-yl-1-oxa-3-azonia-2-azanidacyclopent-3-en-5-imine;hydrochloride Chemical compound Cl.[N-]1OC(=N)C=[N+]1N1CCOCC1 NCGICGYLBXGBGN-UHFFFAOYSA-N 0.000 claims description 5
- 239000000446 fuel Substances 0.000 claims description 3
- 230000000740 bleeding effect Effects 0.000 abstract description 6
- 238000000926 separation method Methods 0.000 description 9
- 230000014509 gene expression Effects 0.000 description 5
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 239000000470 constituent Substances 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000001816 cooling Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000000116 mitigating effect Effects 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 230000001105 regulatory effect 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
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D19/00—Axial-flow pumps
- F04D19/02—Multi-stage pumps
-
- 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
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
- F02C3/06—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
-
- 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
- F02C7/14—Cooling of plants of fluids in the plant, e.g. lubricant or fuel
- F02C7/141—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid
- F02C7/143—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid before or between the compressor stages
-
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
- F04D17/08—Centrifugal pumps
- F04D17/10—Centrifugal pumps for compressing or evacuating
- F04D17/12—Multi-stage pumps
- F04D17/122—Multi-stage pumps the individual rotor discs being, one for each stage, on a common shaft and axially spaced, e.g. conventional centrifugal multi- stage compressors
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/541—Specially adapted for elastic fluid pumps
Definitions
- the present disclosure relates to a multistage axial compressor and a gas turbine.
- a working fluid for example air
- the flow of a working fluid becomes unstable during low-speed rotation, for example, during start-up operation or during deceleration operation for stopping.
- a means for avoiding such a situation there is one that adopts an extraction structure.
- an extraction chamber, a main flow path, a communication path, and an extraction nozzle are formed in a compressor casing, and an extraction pipe is connected to the extraction nozzle.
- the extraction pipe is provided with a flow rate control valve, and by adjusting the opening degree of the flow rate control valve, the air in the middle of compression flowing through the main flow path passes through the communication path, the extraction chamber, the extraction nozzle and the extraction piping, and the compressor Bleed out of casing.
- the first surface on the circumferential side and the second surface on the other side in the circumferential direction around the rotation axis on the inner circumferential surface of the extraction nozzle has a direction change mitigation portion that gradually extends in a direction approaching the other surface in the circumferential direction from the radially outer surface of the extraction chamber toward the radially outer side.
- the air turns around the rotation axis toward the other side in the circumferential direction, that is, toward the side where the compressor rotor rotates.
- the compressed air that has flowed through the extraction chamber toward the other side in the circumferential direction along the radial outer surface of the extraction chamber reaches the extraction chamber side opening of the extraction nozzle. Also, it flows along the direction change relaxation portion in the first surface, and can flow into the extraction nozzle with almost no separation from the radially outer surface of the extraction chamber and the first surface of the extraction nozzle.
- connection angle of the bleed nozzle to the bleed chamber is important, but Patent Document 1 does not specifically describe the connection angle.
- an object of at least one embodiment of the present invention is to provide a multistage axial compressor and a gas turbine that can increase the extraction flow rate and can operate stably even at a low speed.
- a multistage axial compressor is: A rotating shaft with a plurality of blades attached thereto; A casing that surrounds the rotating shaft, and a casing that forms a flow path of a working fluid between the rotating shaft and the casing; An annular wall extending in the circumferential direction of the rotating shaft so as to surround the casing, and a wall forming an annular bleed chamber communicating with the flow path; A plurality of port portions connected to the outer peripheral surface of the wall portion, and a plurality of port portions each forming an outlet channel communicating with the extraction chamber; A plurality of bleed pipes respectively connected to the plurality of port portions; Of the two corner regions where the inner surface of the port portion and the inner surface of the wall portion intersect with each other when viewed in a cross section orthogonal to the rotation axis, the corner region located on the rear side in the rotation direction of the working fluid in the extraction chamber And when the angle formed by the inner surface of the port portion and the inner surface of the wall portion is ⁇ 1, The angle formed by the inner surface of the port portion and
- the multistage axial flow compressor having the above configuration (1) can operate stably even at a low speed.
- the corner region located on the front side in the rotation direction of the working fluid in the extraction chamber, as seen in a cross section orthogonal to the rotation axis When the angle formed by the inner surface of the port portion and the inner surface of the wall portion is ⁇ 2, The angle ⁇ 2 is 315 ° or more.
- the multistage axial flow compressor having the above configuration (2) can operate stably even at a low speed.
- the angle ⁇ 1 is given by the following formula: 270 ° ⁇ sin ⁇ 1 ((1 ⁇ d / D) ⁇ 0.5) ⁇ 180 ° / ⁇ ⁇ ⁇ 1 Satisfy the relationship indicated by The angle ⁇ 2 is given by the following formula: ⁇ 2 ⁇ 270 ° + sin ⁇ 1 ((1 ⁇ d / D) ⁇ 0.5) ⁇ 180 ° / ⁇ The relationship indicated by is satisfied.
- the angle ⁇ 1 is preferably as small as possible to prevent separation of the flow of the working fluid, but cannot be smaller than the angle (tangential direction angle) when the port portion is connected in the tangential direction with respect to the extraction chamber.
- the tangential angle in the rear corner area in the rotational direction of the working fluid expressed according to the definition of the angle ⁇ 1 is ⁇ t1
- ⁇ t1 270 ° ⁇ sin ⁇ 1 ((1-d / D) ⁇ 0 .5) ⁇ 180 ° / ⁇
- the tangential direction angle ⁇ t1 can be determined based on the outer diameter of the extraction chamber and the inner diameter of the port portion.
- the minimum value of the angle ⁇ 1 is set to the tangential angle ⁇ t1 based on the outer diameter of the extraction chamber and the inner diameter of the port portion.
- the angle ⁇ 2 is preferably as large as possible to facilitate the flow of the working fluid from the extraction chamber to the port portion.
- the maximum value of the angle ⁇ 2 is set to the tangential angle ⁇ t2 based on the outer diameter of the extraction chamber and the inner diameter of the port portion.
- At least one of the plurality of extraction tubes has at least one curved portion;
- the inner diameter of the port portion viewed in a cross section orthogonal to the rotation axis is d,
- R radius of curvature of the at least one curved portion
- the ratio R / d of the radius of curvature R of the curved portion to the inner diameter d of the port portion is expressed by the following formula: 2 ⁇ R / d The relationship indicated by is satisfied.
- the ratio R / d of the curvature radius R of the curved portion to the inner diameter d of the port portion is 2 or more, the pressure loss of the working fluid in the bleed pipe is reduced, and the working fluid is The bleed pipe can flow smoothly. For this reason, the flow rate of the working fluid flowing through the bleed pipe, that is, the bleed flow rate can be increased, and the multistage axial compressor having the above configuration (4) can operate stably even at low speed rotation with a simple configuration. It is.
- the rotating shaft extends in a horizontal direction;
- the plurality of port parts include a first port part, a second port part, a third port part, and a fourth port part,
- the first port portion, the second port portion, the third port portion, and the fourth port portion are arranged in this order in the circumferential direction of the rotation shaft,
- the first port part and the second port part are located on the first side with respect to the center of the rotation axis in a horizontal direction orthogonal to the rotation axis, as seen in a cross section orthogonal to the rotation axis.
- the third port part and the fourth port part are a first part opposite to the first side with respect to the center of the rotation axis in a horizontal direction orthogonal to the rotation axis as seen in a cross section orthogonal to the rotation axis.
- the plurality of bleed pipes include a first bleed pipe, a second bleed pipe, a third bleed pipe, and a fourth continuum connected to the first port part, the second port part, the third port part, and the fourth port part, respectively.
- the first bleed pipe and the second bleed pipe extend to the second side with respect to the center of the rotation axis in a horizontal direction orthogonal to the rotation axis as seen in a cross section orthogonal to the rotation axis,
- the at least one bending portion includes a first bending portion constituting a part of the first bleeder tube and a second bending portion constituting a part of the second bleeder tube,
- the first bending portion and the second bending portion are viewed in a cross section orthogonal to the rotation axis so that the rotation direction of the working fluid flowing through the first bending portion and the second bending portion is the same as the rotation direction of the working fluid in the extraction chamber. It is curved.
- the first bending portion and the second bending portion are configured such that the rotation direction of the working fluid flowing through the first bending portion and the second bending portion is the same as the rotation direction of the rotation shaft, as viewed in a cross section orthogonal to the rotation shaft. Since it is curved, the working fluid can smoothly flow through the first bending portion and the second bending portion. Therefore, it is possible to increase the flow rate of the working fluid flowing through the first bleed pipe and the second bleed pipe and the bleed flow rate, and the multistage axial compressor having the above configuration (5) can be rotated at a low speed with a simple configuration. It can operate stably even at times.
- the at least one bending portion includes a third bending portion constituting a part of the third bleed tube and a fourth bending portion constituting a part of the fourth bleed tube,
- the third bending portion and the fourth bending portion are configured such that the rotation direction of the working fluid flowing through the third bending portion and the fourth bending portion is opposite to the rotation direction of the working fluid in the extraction chamber when viewed in a cross section orthogonal to the rotation axis. It is curved.
- the third bending portion and the fourth bending portion are configured such that the rotation direction of the working fluid flowing through the third bending portion and the fourth bending portion is opposite to the rotation direction of the rotation shaft when viewed in a cross section orthogonal to the rotation shaft.
- the ratio R / d is 2 or more, the pressure loss at the third and fourth curved portions is reduced. Therefore, it is possible to increase the flow rate of the working fluid flowing through the third bleed pipe and the fourth bleed pipe, and the bleed flow rate, and the multistage axial compressor having the above configuration (6) rotates at a low speed with a simple configuration. It can operate stably even at times.
- the rotating shaft extends in a horizontal direction;
- the plurality of port parts include a first port part, a second port part, a third port part, and a fourth port part,
- the first port portion, the second port portion, the third port portion, and the fourth port portion are arranged in this order in the circumferential direction of the rotation shaft,
- the first port part and the second port part are located on the first side with respect to the center of the rotation axis in a horizontal direction orthogonal to the rotation axis, as seen in a cross section orthogonal to the rotation axis.
- the third port part and the fourth port part are a first part opposite to the first side with respect to the center of the rotation axis in a horizontal direction orthogonal to the rotation axis as seen in a cross section orthogonal to the rotation axis. Located on the 2 side, The first port portion and the third port portion extend along a horizontal direction orthogonal to the rotation axis, The second port portion and the fourth port portion extend along the vertical direction.
- the first port portion and the third port portion extend in the horizontal direction
- the second port portion and the fourth port portion extend in the vertical direction.
- the separation of the flow of the working fluid flowing into the first port portion, the second port portion, the third port portion, and the fourth port portion can be prevented.
- the multistage axial compressor having the above configuration (7) can ensure a sufficient extraction flow rate even at low speed rotation with a simple configuration, and can operate stably.
- the rotating shaft extends in a horizontal direction;
- the plurality of port parts include a first port part, a second port part, a third port part, and a fourth port part,
- the intersection of the outer peripheral surface of the wall portion and the axis of the first port portion is at a circumferential position of 30 ° or more and 60 ° or less
- the intersection of the outer peripheral surface of the wall portion and the axis of the second port portion is at a circumferential position of 120 ° to 150 °
- the intersection of the outer peripheral surface of the wall portion and the axis of the third port portion is at a circumferential position of 200 ° to 230 °
- the intersection of the outer peripheral surface of the wall portion and the axis of the fourth port portion is at a circumferential position of 290
- the intersection between the outer peripheral surface of the wall portion and the axis of the first port portion is in a circumferential position of 30 ° or more and 60 ° or less, and the outer peripheral surface of the wall portion and the second port portion.
- the intersecting point with the axial line is at a circumferential position of 120 ° or more and 150 ° or less, and the intersecting point of the outer peripheral surface of the wall portion and the axis line of the third port portion is at a circumferential position of 200 ° or more and 230 ° or less.
- the intersection of the outer peripheral surface of the first portion and the axis of the fourth port portion is at a circumferential position of 290 ° or more and 320 ° or less, the height of the extraction tube in the vertical direction can be suppressed. As a result, the installation space of the multistage axial compressor having the configuration (8) can be reduced.
- the rotating shaft extends in a horizontal direction;
- the plurality of port parts include a first port part, a second port part, a third port part, and a fourth port part,
- the first port part, the second port part, the third port part, and the fourth port part are arranged in this order in the circumferential direction of the rotation shaft,
- the first port part and the second port part are located on the first side with respect to the center of the rotation axis in a horizontal direction orthogonal to the rotation axis, as seen in a cross section orthogonal to the rotation axis.
- the third port part and the fourth port part are a first part opposite to the first side with respect to the center of the rotation axis in a horizontal direction orthogonal to the rotation axis as seen in a cross section orthogonal to the rotation axis.
- the plurality of bleed pipes include a first bleed pipe, a second bleed pipe, a third bleed pipe, and a fourth continuum connected to the first port part, the second port part, the third port part, and the fourth port part, respectively.
- Including a bleed tube When the cross section perpendicular to the rotation axis is divided into four quadrants with the center of the rotation axis as the origin and the vertical and horizontal axes, The distal ends of the first bleeder tube, the second bleeder tube, the third bleeder tube, and the fourth bleeder tube located far from the bleed chamber are located in the same quadrant of the four quadrants. is doing.
- the connection is easy.
- Distal ends of the first bleeder tube, the second bleeder tube, the third bleeder tube, and the fourth bleeder tube are positioned outside the casing in a horizontal direction orthogonal to the rotation axis. .
- a concrete base or the like for supporting the casing may be arranged below the casing. For this reason, it is difficult to arrange the axial piping extending in the axial direction of the rotating shaft below the casing.
- the distal ends of the first bleeder tube, the second bleeder tube, the third bleeder tube, and the fourth bleeder tube are located in the same quadrant, and the casing in the horizontal direction. Since the first bleed pipe, the second bleed pipe, the third bleed pipe, and the fourth bleed pipe are connected to the distal ends of the first bleed pipe, the axial pipe extending in the axial direction of the rotary shaft, and easy.
- a gas turbine includes: A multistage axial compressor, A combustor capable of generating combustion gas by burning fuel using air compressed by the multistage axial flow compressor;
- the multistage axial compressor is: A rotating shaft with a plurality of blades attached thereto; A casing surrounding the rotating shaft, the casing forming a flow path of the air as a working fluid between the rotating shaft and the casing; An annular wall extending in the circumferential direction of the rotating shaft so as to surround the casing, and a wall forming an annular bleed chamber communicating with the flow path; A plurality of port portions connected to the outer peripheral surface of the wall portion, and a plurality of port portions each forming an outlet channel communicating with the extraction chamber; A plurality of bleed pipes respectively connected to the plurality of port portions; Of the two corner regions where the inner surface of the port portion and the inner surface of the wall portion intersect with each other when viewed
- the angle ⁇ 1 is 225 ° or less, when the working fluid flows into the port portion from the extraction chamber, separation of the flow of the working fluid in the corner area on the rear side in the rotation direction is prevented. The For this reason, the pressure loss of the fluid when flowing from the extraction chamber into the port portion is reduced, the working fluid flows smoothly from the extraction chamber into the port portion, and the extraction flow rate is increased.
- the multistage axial compressor can operate stably even at low speeds, and the gas turbine having the above-described configuration (11) is also stable at low speeds, for example, during start-up and deceleration for stopping. It is possible to operate.
- a multistage axial flow compressor and a gas turbine that can increase the extraction flow rate and can operate stably even at a low speed.
- FIG. 3 is a schematic sectional view taken along line III-III in FIG. 2.
- FIG. 4 is an enlarged view of a region IV in FIG. 3.
- FIG. 4 is a schematic cross-sectional view corresponding to FIG. 3 of a multistage axial flow compressor according to another embodiment.
- an expression indicating that things such as “identical”, “equal”, and “homogeneous” are in an equal state not only represents an exactly equal state, but also has a tolerance or a difference that can provide the same function. It also represents the existing state.
- expressions representing shapes such as quadrangular shapes and cylindrical shapes represent not only geometrically strict shapes such as quadrangular shapes and cylindrical shapes, but also concave projections and chamfers as long as the same effects can be obtained. A shape including a part or the like is also expressed.
- the expressions “comprising”, “comprising”, “comprising”, “including”, or “having” one constituent element are not exclusive expressions for excluding the existence of the other constituent elements.
- FIG. 1 is a diagram showing a schematic configuration of a gas turbine 1 according to an embodiment of the present invention.
- FIG. 2 is a diagram showing a schematic configuration of a part of the multistage axial compressors 2a and 2b applied to the gas turbine 1 of FIG.
- FIG. 3 is a schematic cross-sectional view taken along the line III-III in FIG.
- FIG. 4 is an enlarged view of a region IV in FIG.
- FIG. 5 is a schematic cross-sectional view corresponding to FIG. 3 of a multistage axial flow compressor 2b according to another embodiment.
- the multistage axial compressors 2a and 2b are collectively referred to as the multistage axial compressor 2.
- a gas turbine 1 includes a multistage axial compressor 2, a combustor 4, and a turbine 6.
- the combustor 4 can burn fuel using the air compressed by the multistage axial compressor 2 and generate high-temperature combustion gas.
- the turbine 6 can output power using the combustion gas generated in the combustor 4.
- a part of the motive power output from the turbine 6 is supplied to the multistage axial compressor 2, and the remaining part is supplied to, for example, a generator (not shown) and used for power generation.
- the multistage axial flow compressor 2 includes a rotating shaft 10, a casing 12, a wall portion 14, a plurality of port portions 16, and a plurality of extraction pipes 18.
- a plurality of moving blade rows are attached to the rotating shaft 10.
- the plurality of stages of moving blade rows are arranged apart from each other in the axial direction of the rotating shaft 10.
- Each moving blade row includes a plurality of moving blades 20 attached to the rotating shaft 10, and in each moving blade row, the plurality of moving blades 20 are arranged in the circumferential direction of the rotating shaft 10.
- the casing 12 surrounds the rotating shaft 10, and a working fluid flow path 22 is formed between the casing 12 and the rotating shaft 10.
- the working fluid is air.
- a plurality of stages of stationary blade rows are attached to the casing 12.
- the plurality of stages of stationary blade rows are arranged apart from each other in the axial direction of the rotating shaft 10, and the moving blade rows and the stationary blade rows are alternately arranged in the axial direction of the rotating shaft 10.
- Each stationary blade row includes a plurality of stationary blades 24 attached to the casing 12. In each stationary blade row, the plurality of stationary blades 24 are arranged in the circumferential direction of the rotating shaft 10.
- the wall portion 14 extends in the circumferential direction of the rotary shaft 10 so as to surround the casing 12, and an annular space (bleeding chamber) 26 communicating with the flow channel 22 is formed around the flow channel 22.
- the extraction chamber 26 communicates with the flow path 22 via a slit (communication path) 28 formed in the casing 12.
- the extraction chamber 26 communicates with an intermediate portion of the flow path 22 in the axial direction of the rotary shaft 10 so that the working fluid being compressed can be extracted.
- the middle part does not mean the center but means the part excluding both ends.
- the plurality of port portions (bleeding nozzles) 16 are continuous with the outer peripheral surface of the wall portion 14. Each port portion 16 has a hollow cylindrical shape and forms an outlet channel 30 communicating with the extraction chamber 26.
- the plurality of extraction pipes 18 are respectively connected to the plurality of port portions 16.
- the extraction pipe 18 forms a pipe line 32 that is continuous with the outlet flow path 30.
- the port portion 16 may be formed integrally with the wall portion 14 or may be formed integrally with the bleed pipe 18. In the latter case, the end of the bleed pipe 18 may be directly connected to the wall 14 to constitute an outlet channel.
- a plurality of flow rate adjustment valves 19 are inserted in the plurality of extraction pipes 18, respectively, and the flow rate of the working fluid flowing through the extraction pipes 18 can be adjusted by adjusting the opening degree of the flow rate adjustment valve 19.
- the working fluid extracted through the extraction pipe 18 can be used for cooling the turbine 6, for example. 3 and 5, the flow rate adjustment valve 19 is omitted.
- 34b the angle formed by the inner surface 17 of the port portion 16 and the inner surface 15 of the wall portion 14 is defined as ⁇ 1 in the corner region 34a located rearward in the rotation direction Rf of the working fluid in the extraction chamber 26.
- the inner surface 17 of the port portion 16 is formed between the inner surface 15 of the wall portion 14 and the inner surface 17 of the port portion 16 when viewed in a cross section orthogonal to the rotation axis 10.
- intersection points X and Y may be intersections between the inner surface 15 of the wall portion 14 and an extension line of the inner surface 17 of the port portion 16.
- the angle ⁇ 1 defined as described above is 225 ° or less.
- the angle ⁇ 1 is 225 ° or less, when the working fluid flows into the port portion 16 from the extraction chamber 26, the operation in the corner region 34a on the rear side in the rotation direction Rf of the working fluid in the extraction chamber 26 is performed. Separation of fluid flow is prevented. For this reason, the pressure loss of the working fluid when flowing into the port portion 16 from the extraction chamber 26 is reduced, the working fluid smoothly flows into the port portion 16 from the extraction chamber 26, and the extraction flow rate is increased.
- the multistage axial compressor 2 can operate stably even at a low speed, and thus the gas turbine 1 having the above-described configuration is also stable at a low speed, for example, during start-up or during deceleration for stopping. It is possible to operate.
- the working fluid in the extraction chamber 26 is out of the two corner regions 34 a and 34 b where the inner surface 17 of the port portion 16 and the inner surface 15 of the wall portion 14 intersect.
- the angle formed by the inner surface 17 of the port portion 16 and the inner surface 15 of the wall portion 14 is defined as ⁇ 2 in the corner region 34b located on the front side in the rotation direction Rf, the angle ⁇ 2 is 315 ° or more.
- the inner surface 17 of the port portion 16 is formed between the inner surface 15 of the wall portion 14 and the inner surface 17 of the port portion 16 when viewed in a cross section orthogonal to the rotation axis 10. It is defined by a line L connecting the two intersections X and Y.
- the intersection points X and Y may be intersections between the inner surface 15 of the wall portion 14 and an extension line of the inner surface 17 of the port portion 16.
- the multistage axial compressor 2 having the above-described configuration can operate stably even at a low speed.
- the inner diameter of the port portion 16 viewed in a cross section orthogonal to the rotation axis 10 is defined as d, and as shown in FIGS.
- the angle ⁇ 1 is expressed by the following formula: 270 ° ⁇ sin ⁇ 1 ((1 ⁇ d / D) ⁇ 0.5) ⁇ 180 ° / ⁇ ⁇ ⁇ 1
- the angle ⁇ 2 is expressed by the following formula: ⁇ 2 ⁇ 270 ° + sin ⁇ 1 ((1 ⁇ d / D) ⁇ 0.5) ⁇ 180 ° / ⁇
- the relationship indicated by is satisfied.
- the angle ⁇ 2 is preferably as large as possible to facilitate the flow of the working fluid from the bleed chamber 26 to the port portion 16, but the angle when the port portion 16 is continuous in the tangential direction with respect to the bleed chamber 26. It cannot be larger than (tangential direction angle).
- the port portion 16 has a cylindrical shape with a constant inner diameter d. Note that the corner region 34b located on the front side in the direction of rotation Rf of the working fluid as viewed in a cross section orthogonal to the rotating shaft 10 may be subjected to R machining, and the inner surface 17 and the wall portion 14 of the port portion 16 may be processed. The inner surface 15 may be connected via a curved surface 35.
- At least one extraction tube of the plurality of extraction tubes 18 has at least one curved portion 36.
- the radius of curvature of the curved portion 36 is R
- the ratio R / d of the radius of curvature R of the curved portion 36 with respect to the inner diameter d of the port portion 16 (or the inner diameter of the extraction tube 18) is: 2 ⁇ R / d
- the relationship indicated by is satisfied.
- the multistage axial compressor 2 having the above-described configuration can operate stably even at low-speed rotation with a simple configuration.
- the radius of curvature R of the curved portion 36 is the radius of curvature at the tube axis (center line of the curved portion 36).
- the rotating shaft 10 extends in the horizontal direction as shown in FIG.
- the plurality of port portions 16 include a first port portion 16a, a second port portion 16b, a third port portion 16c, and a fourth port portion 16d.
- the first port portion 16a, the second port portion 16b, the third port portion 16c, and the fourth port portion 16d are arranged in this order in the circumferential direction of the rotating shaft 10.
- the first port portion 16 a and the second port portion 16 b are located on the first side with respect to the center C of the rotation shaft 10 in the horizontal direction orthogonal to the rotation shaft 10 when viewed in a cross section orthogonal to the rotation shaft 10. .
- the third port portion 16c and the fourth port portion 16d are viewed from a cross section orthogonal to the rotation shaft 10, and are opposite to the first side with respect to the center C of the rotation shaft 10 in the horizontal direction orthogonal to the rotation shaft 10. Located on the 2 side.
- the plurality of bleed pipes 18 are a first bleed pipe 18a, a second bleed pipe 18b, and a third bleed pipe 18c respectively connected to the first port portion 16a, the second port portion 16b, the third port portion 16c, and the fourth port portion 16d. And a fourth extraction pipe 18d.
- the first bleed pipe 18a and the second bleed pipe 18b extend to the second side with respect to the center C of the rotary shaft 10 in the horizontal direction perpendicular to the rotary shaft 10 when viewed in a cross section orthogonal to the rotary shaft 10. Yes.
- the at least one bending portion 36 includes first bending portions 36a1 and 36a2 that constitute a part of the first extraction tube 18a, and a second portion that constitutes a part of the second extraction tube 18b. 2 curved portions 36b.
- the first bending portions 36 a 1, 36 a 2 and the second bending portion 36 b are such that the rotation direction of the working fluid flowing through the first bending portions 36 a 1, 36 a 2 and the second bending portion 36 b is the same as the rotation direction Rf of the working fluid in the extraction chamber 26. Is curved.
- the first bending portions 36a1 and 36a2 and the second bending portion 36b have the rotation direction of the working fluid flowing through the first bending portions 36a1 and 36a2 and the second bending portion 36b perpendicular to the rotation shaft 10 in the bleed chamber 26. Therefore, the working fluid can smoothly flow through the first bending portions 36a1 and 36a2 and the second bending portion 36b. For this reason, it is possible to increase the flow rate of the working fluid flowing through the first extraction pipe 18a and the second extraction pipe 18b, that is, the extraction flow rate. As a result, the multistage axial compressor 2b having the above-described configuration can operate stably even at low speed rotation with a simple configuration.
- the at least one bending portion 36 includes a third bending portion 36c that constitutes a part of the third extraction tube 18c, and a fourth bending portion 36d that constitutes a portion of the fourth extraction tube 18d. including.
- the third bending portion 36 c and the fourth bending portion 36 d are bent so that the rotation direction of the working fluid flowing through the third bending portion 36 c and the fourth bending portion 36 d is opposite to the rotation direction Rf of the working fluid in the extraction chamber 26. is doing.
- the third bending portion 36c and the fourth bending portion 36d have the rotation direction of the working fluid flowing through the third bending portion 36c and the fourth bending portion 36d opposite to the rotation direction Rf of the working fluid in the extraction chamber 26, Although it is curved so as to be in the direction, since the ratio R / d is 2 or more, the pressure loss in the third bending portion 36c and the fourth bending portion 36d is reduced. For this reason, it is possible to increase the flow rate of the working fluid flowing through the third extraction tube 18c and the fourth extraction tube 18d, that is, the extraction flow rate. As a result, the multistage axial compressor 2b having the above-described configuration can operate stably even at low speed rotation with a simple configuration.
- the rotating shaft 10 extends in the horizontal direction.
- the plurality of port portions 16 include a first port portion 16a, a second port portion 16b, a third port portion 16c, and a fourth port portion 16d.
- the first port portion 16a, the second port portion 16b, the third port portion 16c, and the fourth port portion 16d are arranged in this order in the circumferential direction of the rotating shaft 10.
- the first port portion 16a and the second port portion 16b are located on the first side with respect to the center C of the rotation shaft 10 in the horizontal direction orthogonal to the rotation shaft 10 when viewed in a cross section orthogonal to the rotation shaft 10.
- the third port portion 16c and the fourth port portion 16d are a second portion opposite to the first side with respect to the center C of the rotation shaft 10 in the horizontal direction orthogonal to the rotation shaft 10 when viewed in a cross section orthogonal to the rotation shaft 10. Located on the side. As shown in FIGS. 3 and 5, the first port portion 16a and the third port portion 16c extend along the horizontal direction orthogonal to the rotation shaft 10, and the second port portion 16b and the fourth port. The part 16d extends along the vertical direction.
- the first port portion 16a and the third port portion 16c extend in the horizontal direction
- the second port portion 16b and the fourth port portion 16d extend in the vertical direction.
- separation of the flow of the working fluid flowing into the first port portion 16a, the second port portion 16b, the third port portion 16c, and the fourth port portion 16d can be prevented.
- the multistage axial compressor 2 having the above-described configuration can ensure a sufficient extraction flow rate even at low speed rotation with a simple configuration, and can operate stably.
- the rotating shaft 10 extends in the horizontal direction, as shown in FIG.
- the plurality of port portions 16 include a first port portion 16a, a second port portion 16b, a third port portion 16c, and a fourth port portion 16d.
- the circumferential position of the top of the outer peripheral surface of the wall 14 is defined as 0 °.
- an intersection of the outer peripheral surface of the wall portion 14 and the axis (center line) of the port portion 16 is defined as Z in a cross section orthogonal to the rotation axis 10.
- the intersection Z between the outer peripheral surface of the wall portion 14 and the axis of the first port portion 16a is in a circumferential position of 30 ° or more and 60 ° or less, and the outer peripheral surface of the wall portion 14 and the second port portion.
- the intersection Z with the axis of 16b is at a circumferential position of 120 ° or more and 150 ° or less, and the intersection Z between the outer peripheral surface of the wall portion 14 and the axis of the third port portion 16c is a circumferential position of 200 ° or more and 230 ° or less.
- the intersection Z between the outer peripheral surface of the wall portion 14 and the axis of the fourth port portion 16d is at a circumferential position of 290 ° to 320 °.
- the intersection Z of the outer peripheral surface of the wall part 14 and the axis line of the 1st port part 16a exists in the circumferential direction position of 30 degrees or more and 60 degrees or less, and the outer peripheral surface of the wall part 14 and the 2nd port part 16b. Is at a circumferential position of 120 ° to 150 °, and the intersection Z of the outer peripheral surface of the wall portion 14 and the axis of the third port portion 16c is at a circumferential position of 200 ° to 230 °.
- the rotating shaft 10 extends in the horizontal direction, and the cross section orthogonal to the rotating shaft 10 is divided into four quadrants with the center C of the rotating shaft 10 as the origin and the vertical and horizontal axes.
- the other ends 37a, 37b, 37c, and 37d of the first extraction pipe 18a, the second extraction pipe 18b, the third extraction pipe 18c, and the fourth extraction pipe 18d are the same.
- the other ends 37 a, 37 b, 37 c, and 37 d of the first bleed pipe 18 a, the second bleed pipe 18 b, the third bleed pipe 18 c, and the fourth bleed pipe 18 d are distal ends viewed from the bleed chamber 26.
- the 1st extraction pipe 18a and the 2nd extraction pipe 18b may merge, and the 3rd extraction pipe 18c and the 4th extraction pipe 18d may merge.
- the other end of the first merging pipe 38a formed by joining the first bleed pipe 18a and the second bleed pipe 18b, and the third bleed pipe 18c and the fourth bleed pipe 18d are joined.
- the other end of the second joining pipe 38b may be located in the same quadrant.
- the other ends 37a, 37b, 37c, and 37d of the first bleeder pipe 18a, the second bleeder pipe 18b, the third bleeder pipe 18c, and the fourth bleeder pipe 18d are located in the same quadrant.
- Pipes extending in the axial direction of the rotary shaft 10 to the other ends 37a, 37b, 37c, 37d of the first extraction pipe 18a, the second extraction pipe 18b, the third extraction pipe 18c, and the fourth extraction pipe 18d (axial direction)
- the connection is easy.
- the other ends 37 a, 37 b, 37 c, and 37 d of the first bleeder pipe 18 a, the second bleeder pipe 18 b, the third bleeder pipe 18 c, and the fourth bleeder pipe 18 d have cross sections orthogonal to the rotation shaft 10. Are located in the same quadrant and are located outside the casing 12 in the horizontal direction perpendicular to the rotation axis 10. A concrete base or the like for supporting the casing 12 may be disposed below the casing 12. For this reason, it is difficult to arrange the axial piping 40 extending in the axial direction of the rotating shaft 10 below the casing 12.
- the other ends 37a, 37b, 37c, and 37d of the first extraction pipe 18a, the second extraction pipe 18b, the third extraction pipe 18c, and the fourth extraction pipe 18d are located in the same quadrant. And since it is located outside the casing 12 in the horizontal direction, the other ends 37a, 37b, 37c of the first extraction pipe 18a, the second extraction pipe 18b, the third extraction pipe 18c, and the fourth extraction pipe 18d, It is easy to connect the axial pipe 40 extending in the axial direction of the rotary shaft 10 to 37d.
- the other ends 37 a, 37 b, 37 c, and 37 d of the first bleed pipe 18 a, the second bleed pipe 18 b, the third bleed pipe 18 c, and the fourth bleed pipe 18 d are more than the center C of the rotating shaft 10. It is located in the same quadrant located below.
- the ratio d / D of the inner diameter d of the port portion 16 to the outer diameter D of the extraction chamber 26 is 1/20 or more and 1/2 or less when viewed in a cross section orthogonal to the rotation shaft 10.
- the port portion 16 includes only the first port portion 16a, the second port portion 16b, the third port portion 16c, and the fourth port portion 16d, as shown in FIGS.
- the number of port parts 16 is not necessarily limited to four.
- the rotation direction Rf of the working fluid in the extraction chamber 26 is the same as the rotation direction of the rotation shaft 10. Usually, the rotation direction Rf of the working fluid in the extraction chamber 26 matches the rotation direction of the rotating shaft 10. In some embodiments, the rotation direction Rf of the working fluid in the extraction chamber 26 is opposite to the rotation direction of the rotation shaft 10. Depending on the shape of the stationary blade 24 and the position of the slit 28, the rotation direction Rf of the working fluid in the extraction chamber 26 may be opposite to the rotation direction of the rotary shaft 10.
- the present invention is not limited to the above-described embodiments, and includes forms obtained by changing the above-described embodiments and forms obtained by combining these forms.
- the multistage axial flow compressor 2 can be applied to compression of a working fluid other than air.
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Abstract
Description
例えば、特許文献1が開示する回転機械では、圧縮機ケーシングに、抽気室、主流路、連通路及び抽気ノズルが形成されており、抽気ノズルには抽気配管が接続されている。抽気配管には流量調節弁が設けられ、流量調節弁の開度を調整することによって、主流路を流れている圧縮途中の空気が、連通路、抽気室、抽気ノズル及び抽気配管を通じて、圧縮機ケーシングの外へと抽気される。
ここで、環形状の連通路及び抽気室内では、空気が回転軸線を中心として周方向の他方側に向かって、つまり圧縮機ロータが回転する側に向かって旋回する。
このように空気が旋回していても、抽気室内をこの抽気室の径方向外側面に沿って周方向の他方側に向かって流れてきた圧縮空気は、この抽気ノズルの抽気室側開口に至っても、第一面中の方向変換緩和部に沿って流れ、抽気室の径方向外側面及び抽気ノズルの第一面からほとんど剥離することなく、抽気ノズル内に流入することができる。
複数の動翼が取り付けられた回転軸と、
前記回転軸を囲むケーシングであって、前記回転軸と前記ケーシングとの間に作動流体の流路を形成するケーシングと、
前記ケーシングを囲むように前記回転軸の周方向に延在する環形状の壁部であって、前記流路と連通する環形状の抽気室を形成する壁部と、
前記壁部の外周面に連なる複数のポート部であって、それぞれ前記抽気室と連通する出口流路を形成する複数のポート部と、
前記複数のポート部にそれぞれ連なる複数の抽気管と
を備え、
前記回転軸と直交する断面でみて、前記ポート部の内面と前記壁部の内面とが交わる2つのコーナ領域のうち、前記抽気室における前記作動流体の回転方向にて後方側に位置するコーナ領域にて、前記ポート部の内面と前記壁部の内面とがなす角度をθ1としたとき、
前記角度θ1は225°以下である。
前記回転軸と直交する断面でみて、前記ポート部の内面と前記壁部の内面とが交わる2つのコーナ領域のうち、前記抽気室における前記作動流体の回転方向にて前方側に位置するコーナ領域にて、前記ポート部の内面と前記壁部の内面とがなす角度をθ2としたとき、
前記角度θ2は315°以上である。
前記回転軸と直交する断面でみた前記ポート部の内径をdとし、且つ、前記抽気室の外径をDとしたとき、
前記角度θ1は、次式:
270°-sin-1((1―d/D)^0.5)・180°/π≦θ1
で示される関係を満たし、
前記角度θ2は、次式:
θ2≦270°+sin-1((1―d/D)^0.5)・180°/π
で示される関係を満たしている。
同様に、角度θ2は、抽気室からポート部への作動流体の流れを円滑にするためには大きいほどよいが、抽気室に対しポート部が接線方向に連なっているときの角度(接線方向角度)よりも大きくすることはできない。上記した角度θ2の定義に従って表した、作動流体の回転方向にて前方側のコーナ領域での接線方向角度をθt2とすると、θt2=270°+sin-1((1―d/D)^0.5)・180°/πであり、接線方向角度θt2は、抽気室の外径及びポート部の内径に基づいて決定することができる。そこで、上記構成(3)では、抽気室の外径及びポート部の内径に基づいて角度θ2の最大値を接線方向角度θt2に設定している。
前記複数の抽気管のうち少なくとも1つの抽気管は少なくとも1つの湾曲部を有し、
前記回転軸と直交する断面でみた前記ポート部の内径をdとし、
前記少なくとも1つの湾曲部の曲率半径をRとしたとき、
前記ポート部の内径dに対する前記湾曲部の曲率半径Rの比R/dは、次式:
2≦R/d
で示される関係を満たしている。
前記回転軸は水平方向に延在し、
前記複数のポート部は、第1ポート部、第2ポート部、第3ポート部及び第4ポート部を含み、
前記第1ポート部、前記第2ポート部、前記第3ポート部及び前記第4ポート部は、前記回転軸の周方向にて、この順序で配列され、
前記第1ポート部及び前記第2ポート部は、前記回転軸と直交する断面でみて、前記回転軸と直交する水平方向にて前記回転軸の中心に対し第1の側に位置し、
前記第3ポート部及び前記第4ポート部は、前記回転軸と直交する断面でみて、前記回転軸と直交する水平方向にて前記回転軸の中心に対し前記第1の側とは反対の第2の側に位置し、
前記複数の抽気管は、前記第1ポート部、前記第2ポート部、前記第3ポート部及び前記第4ポート部にそれぞれ連なる第1抽気管、第2抽気管、第3抽気管及び第4抽気管を含み、
前記第1抽気管及び前記第2抽気管は、前記回転軸と直交する断面でみて、前記回転軸と直交する水平方向にて前記回転軸の中心に対し前記第2の側まで延在し、
前記少なくとも1つの湾曲部は、前記第1抽気管の一部を構成する第1湾曲部と、前記第2抽気管の一部を構成する第2湾曲部とを含み、
前記第1湾曲部及び前記第2湾曲部は、前記回転軸と直交する断面でみて、自身を流れる前記作動流体の回転方向が前記抽気室における前記作動流体の回転方向と同じ方向になるように湾曲している。
前記少なくとも1つの湾曲部は、前記第3抽気管の一部を構成する第3湾曲部と、前記第4抽気管の一部を構成する第4湾曲部とを含み、
前記第3湾曲部及び前記第4湾曲部は、前記回転軸と直交する断面でみて、自身を流れる前記作動流体の回転方向が前記抽気室における前記作動流体の回転方向と逆方向になるように湾曲している。
前記回転軸は水平方向に延在し、
前記複数のポート部は、第1ポート部、第2ポート部、第3ポート部及び第4ポート部を含み、
前記第1ポート部、前記第2ポート部、前記第3ポート部及び前記第4ポート部は、前記回転軸の周方向にて、この順序で配列され、
前記第1ポート部及び前記第2ポート部は、前記回転軸と直交する断面でみて、前記回転軸と直交する水平方向にて前記回転軸の中心に対し第1の側に位置し、
前記第3ポート部及び前記第4ポート部は、前記回転軸と直交する断面でみて、前記回転軸と直交する水平方向にて前記回転軸の中心に対し前記第1の側とは反対の第2の側に位置し、
前記第1ポート部及び前記第3ポート部は、前記回転軸と直交する水平方向に沿って延在し、
前記第2ポート部及び前記第4ポート部は、鉛直方向に沿って延在している。
前記回転軸は水平方向に延在し、
前記複数のポート部は、第1ポート部、第2ポート部、第3ポート部及び第4ポート部を含み、
前記回転軸と直交する断面にて、前記壁部の外周面の頂部の周方向位置を0°としたときに、
前記壁部の外周面と前記第1ポート部の軸線との交点は30°以上60°以下の周方向位置にあり、
前記壁部の外周面と前記第2ポート部の軸線との交点は120°以上150°以下の周方向位置にあり、
前記壁部の外周面と前記第3ポート部の軸線との交点は200°以上230°以下の周方向位置にあり、
前記壁部の外周面と前記第4ポート部の軸線との交点は290°以上320°以下の周方向位置にある。
前記回転軸は水平方向に延在し、
前記複数のポート部は、第1ポート部、第2ポート部、第3ポート部及び第4ポート部を含み、
前記第1ポート部、前記第2ポート部、前記第3ポート部及び前記第4ポート部は、前記回転軸の周方向にて、この順序で配列され、
前記第1ポート部及び前記第2ポート部は、前記回転軸と直交する断面でみて、前記回転軸と直交する水平方向にて前記回転軸の中心に対し第1の側に位置し、
前記第3ポート部及び前記第4ポート部は、前記回転軸と直交する断面でみて、前記回転軸と直交する水平方向にて前記回転軸の中心に対し前記第1の側とは反対の第2の側に位置し、
前記複数の抽気管は、前記第1ポート部、前記第2ポート部、前記第3ポート部及び前記第4ポート部にそれぞれ連なる第1抽気管、第2抽気管、第3抽気管及び第4抽気管を含み、
前記回転軸と直交する断面を、前記回転軸の中心を原点とし、鉛直軸及び水平軸にて4つの象限に分割したときに、
前記抽気室に対し遠方に位置する前記第1抽気管、前記第2抽気管、前記第3抽気管及び前記第4抽気管の遠位端は、前記4つの象限のうち同一の象限内に位置している。
前記第1抽気管、前記第2抽気管、前記第3抽気管及び前記第4抽気管の遠位端は、前記回転軸と直交する水平方向にて、前記ケーシングよりも外側に位置している。
この点、上記構成(10)によれば、第1抽気管、第2抽気管、第3抽気管及び第4抽気管の遠位端は、同一の象限内に位置し、水平方向にてケーシングよりも外側に位置しているので、第1抽気管、第2抽気管、第3抽気管及び第4抽気管の遠位端に、回転軸の軸線方向に延在する軸方向配管を連結し易い。
多段軸流圧縮機と、
前記多段軸流圧縮機によって圧縮された空気を利用して燃料を燃焼させ、燃焼ガスを発生可能な燃焼器と、
前記燃焼器で発生した燃焼ガスを利用して動力を出力可能なタービンと
を備えるガスタービンにおいて、
前記多段軸流圧縮機は、
複数の動翼が取り付けられた回転軸と、
前記回転軸を囲むケーシングであって、前記回転軸と前記ケーシングとの間に作動流体としての前記空気の流路を形成するケーシングと、
前記ケーシングを囲むように前記回転軸の周方向に延在する環形状の壁部であって、前記流路と連通する環形状の抽気室を形成する壁部と、
前記壁部の外周面に連なる複数のポート部であって、それぞれ前記抽気室と連通する出口流路を形成する複数のポート部と、
前記複数のポート部にそれぞれ連なる複数の抽気管と
を備え、
前記回転軸と直交する断面でみて、前記ポート部の内面と前記壁部の内面とが交わる2つのコーナ領域のうち、前記抽気室における前記作動流体の回転方向にて後方側に位置するコーナ領域にて、前記ポート部の内面と前記壁部の内面とがなす角度をθ1としたとき、
前記角度θ1は225°以下である。
例えば、「ある方向に」、「ある方向に沿って」、「平行」、「直交」、「中心」、「同心」或いは「同軸」等の相対的或いは絶対的な配置を表す表現は、厳密にそのような配置を表すのみならず、公差、若しくは、同じ機能が得られる程度の角度や距離をもって相対的に変位している状態も表すものとする。
例えば、「同一」、「等しい」及び「均質」等の物事が等しい状態であることを表す表現は、厳密に等しい状態を表すのみならず、公差、若しくは、同じ機能が得られる程度の差が存在している状態も表すものとする。
例えば、四角形状や円筒形状等の形状を表す表現は、幾何学的に厳密な意味での四角形状や円筒形状等の形状を表すのみならず、同じ効果が得られる範囲で、凹突起や面取り部等を含む形状も表すものとする。
一方、一の構成要素を「備える」、「具える」、「具備する」、「含む」、又は、「有する」という表現は、他の構成要素の存在を除外する排他的な表現ではない。
なお、以下の説明では、多段軸流圧縮機2a,2bを一括して多段軸流圧縮機2とも称する。
燃焼器4は、多段軸流圧縮機2によって圧縮された空気を利用して燃料を燃焼させ、高温の燃焼ガスを発生可能である。
タービン6は、燃焼器4で発生した燃焼ガスを利用して動力を出力可能である。タービン6が出力した動力の一部は、多段軸流圧縮機2に供給され、残部は、例えば発電機(不図示)に供給され、発電に利用される。
回転軸10には、複数段の動翼列が取り付けられている。複数段の動翼列は、回転軸10の軸線方向にて相互に離間して配列されている。各動翼列は、それぞれ回転軸10に取り付けられた複数の動翼20を含み、各動翼列において、複数の動翼20は回転軸10の周方向に配列されている。
また、ケーシング12には、複数段の静翼列が取り付けられている。複数段の静翼列は、回転軸10の軸線方向にて相互に離間して配列され、回転軸10の軸線方向にて、動翼列と静翼列は交互に配置される。各静翼列は、それぞれケーシング12に取り付けられた複数の静翼24を含み、各静翼列において、複数の静翼24は回転軸10の周方向に配列されている。
複数の抽気管18は、複数のポート部16にそれぞれ連なっている。抽気管18は出口流路30に連なる管路32を形成している。なお、ポート部16は、壁部14と一体に形成されていてもよく、あるいは、抽気管18と一体に形成されていてもよい。後者の場合、抽気管18の端部が壁部14に直接接続され、出口流路を構成していてもよい。
複数の抽気管18には複数の流量調整弁19がそれぞれ介挿され、流量調整弁19の開度を調整することにより、抽気管18を流れる作動流体の流量を調整可能である。抽気管18を通じて抽気された作動流体は、例えばタービン6の冷却等に用いることができる。なお、図3及び図5では、流量調整弁19を省略している。
なお、より正確には、本明細書における角度θ1の定義上、ポート部16の内面17は、回転軸10と直交する断面でみて、壁部14の内面15とポート部16の内面17との2つの交点X,Yを通る直線Lによって規定される。コーナ領域34a,34bにR加工が施されている場合には、交点X,Yは、壁部14の内面15とポート部16の内面17の延長線との交点であってもよい。
上記構成では、角度θ1が225°以下であるので、抽気室26からポート部16に作動流体が流入する際、抽気室26における作動流体の回転方向Rfにて後方側のコーナ領域34aでの作動流体の流れの剥離が防止される。このため、抽気室26からポート部16に流入する際の作動流体の圧力損失が低減され、作動流体が抽気室26からポート部16へと円滑に流入し、抽気流量が増大される。この結果として、多段軸流圧縮機2は、低速回転時でも安定に動作可能であり、ひいては上記構成を有するガスタービン1も、低速回転時、例えば起動中や停止のための減速中に、安定に動作可能である。
なお、より正確には、本明細書における角度θ2の定義上、ポート部16の内面17は、回転軸10と直交する断面でみて、壁部14の内面15とポート部16の内面17との2つの交点X,Yを結ぶ線Lによって規定される。コーナ領域34a,34bにR加工が施されている場合には、交点X,Yは、壁部14の内面15とポート部16の内面17の延長線との交点であってもよい。
270°-sin-1((1―d/D)^0.5)・180°/π≦θ1
で示される関係を満たし、角度θ2は、次式:
θ2≦270°+sin-1((1―d/D)^0.5)・180°/π
で示される関係を満たしている。
2≦R/d
で示される関係を満たしている。
なお、湾曲部36の曲率半径Rは、管軸(湾曲部36の中心線)での曲率半径である。
第1ポート部16a、第2ポート部16b、第3ポート部16c及び第4ポート部16dは、回転軸10の周方向にて、この順序で配列されている。第1ポート部16a及び第2ポート部16bは、回転軸10と直交する断面でみて、回転軸10と直交する水平方向にて回転軸10の中心Cに対し第1の側に位置している。第3ポート部16c及び第4ポート部16dは、回転軸10と直交する断面でみて、回転軸10と直交する水平方向にて回転軸10の中心Cに対し第1の側とは反対の第2の側に位置している。
第1ポート部16a及び第2ポート部16bは、回転軸10と直交する断面でみて、回転軸10と直交する水平方向にて回転軸10の中心Cに対し第1の側に位置し、第3ポート部16c及び第4ポート部16dは、回転軸10と直交する断面でみて、回転軸10と直交する水平方向にて回転軸10の中心Cに対し第1の側とは反対の第2の側に位置している。
そして、図3及び図5に示したように、第1ポート部16a及び第3ポート部16cは、回転軸10と直交する水平方向に沿って延在し、第2ポート部16b及び第4ポート部16dは、鉛直方向に沿って延在している。
なお、図3及び図5に示したように、第1抽気管18a及び第2抽気管18bは合流していてもよく、第3抽気管18c及び第4抽気管18dは合流していてもよい。この場合、第1抽気管18a及び第2抽気管18bが合流して形成された第1合流管38aの他端、及び、第3抽気管18c及び第4抽気管18dが合流して形成された第2合流管38bの他端が、同一の象限内に位置していてもよい。
ケーシング12の下方には、ケーシング12を支持するためのコンクリート製の台座等が配置されることがある。このため、回転軸10の軸線方向に延在する軸方向配管40を、ケーシング12の下方に配置するのは困難である。
この点、上記構成によれば、第1抽気管18a、第2抽気管18b、第3抽気管18c及び第4抽気管18dの他端37a,37b,37c,37dは、同一の象限内に位置し、水平方向にてケーシング12よりも外側に位置しているので、第1抽気管18a、第2抽気管18b、第3抽気管18c及び第4抽気管18dの他端37a,37b,37c,37dに、回転軸10の軸線方向に延在する軸方向配管40を連結し易い。
幾つかの実施形態では、第1抽気管18a、第2抽気管18b、第3抽気管18c及び第4抽気管18dの他端37a,37b,37c,37dは、回転軸10の中心Cよりも下方に位置する同一の象限内に位置している。
幾つかの実施形態では、抽気室26における作動流体の回転方向Rfは、回転軸10の回転方向と逆方向である。静翼24の形状やスリット28の位置によっては、抽気室26における作動流体の回転方向Rfが、回転軸10の回転方向と逆方向となることがある。
2 多段軸流圧縮機
4 燃焼器
6 タービン
10 回転軸
12 ケーシング
14 壁部
15 壁部の内面(抽気室の外周面)
16 ポート部(抽気ノズル)
16a 第1ポート部
16b 第2ポート部
16c 第3ポート部
16d 第4ポート部
17 ポート部の内面
18 抽気管
18a 第1抽気管
18b 第2抽気管
18c 第3抽気管
18d 第4抽気管
19 流量調整弁
20 動翼
22 流路
24 静翼
26 抽気室
28 スリット(連通路)
30 出口流路
32 管路
34a 回転方向にて後方側のコーナ領域
34b 回転方向にて前方側のコーナ領域
35 湾曲面
36 湾曲部
36a1,36a2 第1湾曲部
36b 第2湾曲部
36c 第3湾曲部
36d 第4湾曲部
37a 第1抽気管の遠位端
37b 第2抽気管の遠位端
37c 第3抽気管の遠位端
37d 第4抽気管の遠位端
38a 第1合流管
38b 第2合流管
40 配管(軸方向配管)
C 回転軸の中心
d ポート部の内径
D 抽気室の外径
X,Y,Z 交点
L XとYを通る直線
Rf 抽気室における作動流体の回転方向
R 曲率半径
Claims (11)
- 複数の動翼が取り付けられた回転軸と、
前記回転軸を囲むケーシングであって、前記回転軸と前記ケーシングとの間に作動流体の流路を形成するケーシングと、
前記ケーシングを囲むように前記回転軸の周方向に延在する環形状の壁部であって、前記流路と連通する環形状の抽気室を形成する壁部と、
前記壁部の外周面に連なる複数のポート部であって、それぞれ前記抽気室と連通する出口流路を形成する複数のポート部と、
前記複数のポート部にそれぞれ連なる複数の抽気管と
を備え、
前記回転軸と直交する断面でみて、前記ポート部の内面と前記壁部の内面とが交わる2つのコーナ領域のうち、前記抽気室における前記作動流体の回転方向にて後方側に位置するコーナ領域にて、前記ポート部の内面と前記壁部の内面とがなす角度をθ1としたとき、
前記角度θ1は225°以下である
ことを特徴とする多段軸流圧縮機。 - 前記回転軸と直交する断面でみて、前記ポート部の内面と前記壁部の内面とが交わる2つのコーナ領域のうち、前記抽気室における前記作動流体の回転方向にて前方側に位置するコーナ領域にて、前記ポート部の内面と前記壁部の内面とがなす角度をθ2としたとき、
前記角度θ2は315°以上である
ことを特徴とする請求項1に記載の多段軸流圧縮機。 - 前記回転軸と直交する断面でみた前記ポート部の内径をdとし、且つ、前記抽気室の外径をDとしたとき、
前記角度θ1は、次式:
270°-sin-1((1―d/D)^0.5)・180°/π≦θ1
で示される関係を満たし、
前記角度θ2は、次式:
θ2≦270°+sin-1((1―d/D)^0.5)・180°/π
で示される関係を満たしている
ことを特徴とする請求項2に記載の多段軸流圧縮機。 - 前記複数の抽気管のうち少なくとも1つの抽気管は少なくとも1つの湾曲部を有し、
前記回転軸と直交する断面でみた前記ポート部の内径をdとし、
前記少なくとも1つの湾曲部の曲率半径をRとしたとき、
前記ポート部の内径dに対する前記湾曲部の曲率半径Rの比R/dは、次式:
2≦R/d
で示される関係を満たしている
ことを特徴とする請求項1乃至3の何れか1項に記載の多段軸流圧縮機。 - 前記回転軸は水平方向に延在し、
前記複数のポート部は、第1ポート部、第2ポート部、第3ポート部及び第4ポート部を含み、
前記第1ポート部、前記第2ポート部、前記第3ポート部及び前記第4ポート部は、前記回転軸の周方向にて、この順序で配列され、
前記第1ポート部及び前記第2ポート部は、前記回転軸と直交する断面でみて、前記回転軸と直交する水平方向にて前記回転軸の中心に対し第1の側に位置し、
前記第3ポート部及び前記第4ポート部は、前記回転軸と直交する断面でみて、前記回転軸と直交する水平方向にて前記回転軸の中心に対し前記第1の側とは反対の第2の側に位置し、
前記複数の抽気管は、前記第1ポート部、前記第2ポート部、前記第3ポート部及び前記第4ポート部にそれぞれ連なる第1抽気管、第2抽気管、第3抽気管及び第4抽気管を含み、
前記第1抽気管及び前記第2抽気管は、前記回転軸と直交する断面でみて、前記回転軸と直交する水平方向にて前記回転軸の中心に対し前記第2の側まで延在し、
前記少なくとも1つの湾曲部は、前記第1抽気管の一部を構成する第1湾曲部と、前記第2抽気管の一部を構成する第2湾曲部とを含み、
前記第1湾曲部及び前記第2湾曲部は、前記回転軸と直交する断面でみて、自身を流れる前記作動流体の回転方向が前記抽気室における前記作動流体の回転方向と同じ方向になるように湾曲している
ことを特徴とする請求項4に記載の多段軸流圧縮機。 - 前記少なくとも1つの湾曲部は、前記第3抽気管の一部を構成する第3湾曲部と、前記第4抽気管の一部を構成する第4湾曲部とを含み、
前記第3湾曲部及び前記第4湾曲部は、前記回転軸と直交する断面でみて、自身を流れる前記作動流体の回転方向が前記抽気室における前記作動流体の回転方向と逆方向になるように湾曲している
ことを特徴とする請求項5に記載の多段軸流圧縮機。 - 前記回転軸は水平方向に延在し、
前記複数のポート部は、第1ポート部、第2ポート部、第3ポート部及び第4ポート部を含み、
前記第1ポート部、前記第2ポート部、前記第3ポート部及び前記第4ポート部は、前記回転軸の周方向にて、この順序で配列され、
前記第1ポート部及び前記第2ポート部は、前記回転軸と直交する断面でみて、前記回転軸と直交する水平方向にて前記回転軸の中心に対し第1の側に位置し、
前記第3ポート部及び前記第4ポート部は、前記回転軸と直交する断面でみて、前記回転軸と直交する水平方向にて前記回転軸の中心に対し前記第1の側とは反対の第2の側に位置し、
前記第1ポート部及び前記第3ポート部は、前記回転軸と直交する水平方向に沿って延在し、
前記第2ポート部及び前記第4ポート部は、鉛直方向に沿って延在している
ことを特徴とする請求項4乃至6の何れか1項に記載の多段軸流圧縮機。 - 前記回転軸は水平方向に延在し、
前記複数のポート部は、第1ポート部、第2ポート部、第3ポート部及び第4ポート部を含み、
前記回転軸と直交する断面にて、前記壁部の外周面の頂部の周方向位置を0°としたときに、
前記壁部の外周面と前記第1ポート部の軸線との交点は30°以上60°以下の周方向位置にあり、
前記壁部の外周面と前記第2ポート部の軸線との交点は120°以上150°以下の周方向位置にあり、
前記壁部の外周面と前記第3ポート部の軸線との交点は200°以上230°以下の周方向位置にあり、
前記壁部の外周面と前記第4ポート部の軸線との交点は290°以上320°以下の周方向位置にある
ことを特徴とする請求項4乃至7の何れか1項に記載の多段軸流圧縮機。 - 前記回転軸は水平方向に延在し、
前記複数のポート部は、第1ポート部、第2ポート部、第3ポート部及び第4ポート部を含み、
前記第1ポート部、前記第2ポート部、前記第3ポート部及び前記第4ポート部は、前記回転軸の周方向にて、この順序で配列され、
前記第1ポート部及び前記第2ポート部は、前記回転軸と直交する断面でみて、前記回転軸と直交する水平方向にて前記回転軸の中心に対し第1の側に位置し、
前記第3ポート部及び前記第4ポート部は、前記回転軸と直交する断面でみて、前記回転軸と直交する水平方向にて前記回転軸の中心に対し前記第1の側とは反対の第2の側に位置し、
前記複数の抽気管は、前記第1ポート部、前記第2ポート部、前記第3ポート部及び前記第4ポート部にそれぞれ連なる第1抽気管、第2抽気管、第3抽気管及び第4抽気管を含み、
前記回転軸と直交する断面を、前記回転軸の中心を原点とし、鉛直軸及び水平軸にて4つの象限に分割したときに、
前記抽気室に対し遠方に位置する前記第1抽気管、前記第2抽気管、前記第3抽気管及び前記第4抽気管の遠位端は、前記4つの象限のうち同一の象限内に位置している
ことを特徴とする請求項4乃至8の何れか1項に記載の多段軸流圧縮機。 - 前記第1抽気管、前記第2抽気管、前記第3抽気管及び前記第4抽気管の遠位端は、前記回転軸と直交する水平方向にて、前記ケーシングよりも外側に位置している
ことを特徴とする請求項9に記載の多段軸流圧縮機。 - 多段軸流圧縮機と、
前記多段軸流圧縮機によって圧縮された空気を利用して燃料を燃焼させ、燃焼ガスを発生可能な燃焼器と、
前記燃焼器で発生した燃焼ガスを利用して動力を出力可能なタービンと
を備えるガスタービンにおいて、
前記多段軸流圧縮機は、
複数の動翼が取り付けられた回転軸と、
前記回転軸を囲むケーシングであって、前記回転軸と前記ケーシングとの間に作動流体としての前記空気の流路を形成するケーシングと、
前記ケーシングを囲むように前記回転軸の周方向に延在する環形状の壁部であって、前記流路と連通する環形状の抽気室を形成する壁部と、
前記壁部の外周面に連なる複数のポート部であって、それぞれ前記抽気室と連通する出口流路を形成する複数のポート部と、
前記複数のポート部にそれぞれ連なる複数の抽気管と
を備え、
前記回転軸と直交する断面でみて、前記ポート部の内面と前記壁部の内面とが交わる2つのコーナ領域のうち、前記抽気室における前記作動流体の回転方向にて後方側に位置するコーナ領域にて、前記ポート部の内面と前記壁部の内面とがなす角度をθ1としたとき、
前記角度θ1は225°以下である
ことを特徴とするガスタービン。
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PCT/JP2017/008438 WO2017159397A1 (ja) | 2016-03-14 | 2017-03-03 | 多段軸流圧縮機及びガスタービン |
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US (1) | US11199131B2 (ja) |
JP (1) | JP6689105B2 (ja) |
KR (1) | KR102142852B1 (ja) |
CN (1) | CN108779784B (ja) |
DE (1) | DE112017001298T5 (ja) |
WO (1) | WO2017159397A1 (ja) |
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US11713722B2 (en) * | 2020-05-08 | 2023-08-01 | Rolls-Royce Corporation | Gas turbine engine compressor particulate offtake |
KR20230031606A (ko) | 2021-08-27 | 2023-03-07 | 최봉진 | 구동제어장치를 이용한 조류방지시스템 |
CN117634100B (zh) * | 2024-01-25 | 2024-04-30 | 陕西空天信息技术有限公司 | 多级轴流压气机的子午流道获取方法、装置、设备及介质 |
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JPS58108158U (ja) * | 1982-11-11 | 1983-07-23 | 川崎重工業株式会社 | 集塵装置 |
JPH0763199A (ja) * | 1993-08-10 | 1995-03-07 | Abb Manag Ag | 軸流圧縮機から二次空気流を取り出す装置 |
JP2014145265A (ja) * | 2013-01-28 | 2014-08-14 | Mitsubishi Heavy Ind Ltd | 回転機械、及びこれを備えているガスタービン |
US20140286746A1 (en) * | 2013-03-04 | 2014-09-25 | Pratt & Whitney Canada Corp. | Compressor shroud reverse bleed holes |
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US3848636A (en) * | 1972-09-15 | 1974-11-19 | Bendix Corp | Control apparatus particularly for a plurality of compressor bleed valves of a gas turbine engine |
US4463552A (en) * | 1981-12-14 | 1984-08-07 | United Technologies Corporation | Combined surge bleed and dust removal system for a fan-jet engine |
JPS58108158A (ja) | 1981-12-23 | 1983-06-28 | Ricoh Co Ltd | インクジエツト記録装置 |
US8388308B2 (en) * | 2007-10-30 | 2013-03-05 | General Electric Company | Asymmetric flow extraction system |
US20110083444A1 (en) | 2009-10-09 | 2011-04-14 | General Electric Company | Low btu fuel injection system |
US8973372B2 (en) | 2012-09-05 | 2015-03-10 | Siemens Aktiengesellschaft | Combustor shell air recirculation system in a gas turbine engine |
EP2803822B1 (fr) | 2013-05-13 | 2019-12-04 | Safran Aero Boosters SA | Système de prélèvement d'air de turbomachine axiale |
JP6037996B2 (ja) * | 2013-10-17 | 2016-12-07 | 三菱重工業株式会社 | 圧縮機、及びガスタービン |
JP6188069B2 (ja) * | 2013-10-17 | 2017-08-30 | 三菱重工業株式会社 | 圧縮機、及びガスタービン |
US9909497B2 (en) * | 2015-05-07 | 2018-03-06 | United Technologies Corporation | Combined stability and customer bleed with dirt, water and ice rejection |
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2016
- 2016-03-14 JP JP2016050170A patent/JP6689105B2/ja active Active
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2017
- 2017-03-03 DE DE112017001298.8T patent/DE112017001298T5/de active Pending
- 2017-03-03 US US16/083,720 patent/US11199131B2/en active Active
- 2017-03-03 CN CN201780016280.7A patent/CN108779784B/zh active Active
- 2017-03-03 KR KR1020187026010A patent/KR102142852B1/ko active IP Right Grant
- 2017-03-03 WO PCT/JP2017/008438 patent/WO2017159397A1/ja active Application Filing
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
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JPS58108158U (ja) * | 1982-11-11 | 1983-07-23 | 川崎重工業株式会社 | 集塵装置 |
JPH0763199A (ja) * | 1993-08-10 | 1995-03-07 | Abb Manag Ag | 軸流圧縮機から二次空気流を取り出す装置 |
JP2014145265A (ja) * | 2013-01-28 | 2014-08-14 | Mitsubishi Heavy Ind Ltd | 回転機械、及びこれを備えているガスタービン |
US20140286746A1 (en) * | 2013-03-04 | 2014-09-25 | Pratt & Whitney Canada Corp. | Compressor shroud reverse bleed holes |
Also Published As
Publication number | Publication date |
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US11199131B2 (en) | 2021-12-14 |
KR102142852B1 (ko) | 2020-08-10 |
CN108779784B (zh) | 2020-12-08 |
KR20180108816A (ko) | 2018-10-04 |
CN108779784A (zh) | 2018-11-09 |
US20190093554A1 (en) | 2019-03-28 |
JP2017166358A (ja) | 2017-09-21 |
DE112017001298T5 (de) | 2018-11-22 |
JP6689105B2 (ja) | 2020-04-28 |
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