WO2014141825A1 - 燃焼器、及びガスタービン - Google Patents
燃焼器、及びガスタービン Download PDFInfo
- Publication number
- WO2014141825A1 WO2014141825A1 PCT/JP2014/053771 JP2014053771W WO2014141825A1 WO 2014141825 A1 WO2014141825 A1 WO 2014141825A1 JP 2014053771 W JP2014053771 W JP 2014053771W WO 2014141825 A1 WO2014141825 A1 WO 2014141825A1
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- WIPO (PCT)
- Prior art keywords
- cylinder
- outer peripheral
- peripheral surface
- combustor
- main body
- Prior art date
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
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- 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
- F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
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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
- 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
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/46—Combustion chambers comprising an annular arrangement of several essentially tubular flame tubes within a common annular casing or within individual casings
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/54—Reverse-flow combustion chambers
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/00012—Details of sealing devices
Definitions
- the present invention relates to a combustor that burns fuel in compressed air to generate combustion gas, and a gas turbine including the combustor.
- the gas turbine includes a compressor that generates compressed air, a combustor that generates combustion gas by burning fuel in the compressed air, and a turbine that is rotationally driven by the combustion gas.
- the combustor includes an inner cylinder that supplies fuel and air, and a tail cylinder in which a flame is formed by the fuel and air supplied from the inner cylinder and generates combustion gas (for example, Patent Document 1). reference).
- film air is supplied from the gap between the outlet outer ring constituting the tip of the inner tube and the tail tube.
- the structure is known.
- a spacer is attached to the outlet outer ring in order to secure a gap for supplying film air.
- a plurality of spacers are attached to the outer peripheral surface of the outlet outer ring in the circumferential direction. When the spacer abuts against the inner peripheral surface of the tail tube, a gap for supplying film air is uniformly ensured over the entire circumference.
- An object of the present invention is to provide a combustor capable of reducing the manufacturing cost by reducing the number of parts, and a gas turbine including the combustor.
- the combustor includes a first cylinder that supplies fuel and air from an opening at the tip, a flame is formed on the inner peripheral side by the fuel and air, and the tip of the first cylinder is A second cylinder inserted on the inner peripheral side of the base end, and the first cylinder includes a first cylinder main body part and a ring part that forms a distal end of the first cylinder, A cylindrical main body part, and a plurality of circumferentially integrated protrusions projecting radially outward on the outer peripheral surface of the main body part, the outer peripheral surface of the main body part being The cross-sectional shape viewed from the axial direction along the axis of the first cylinder is formed in a polygonal shape within the range in which the convex portion is formed.
- the main body portion and the convex portion are integrally formed in the ring portion, so that the number of parts can be reduced and the manufacturing cost of the combustor can be reduced.
- the outer peripheral surface of the main body which is a processing target
- the number of changes in the relative angle between the processing tool and the processing target is reduced, so that the number of processing steps can be reduced.
- the main body is provided with a polygonal ring part on which the convex part is formed and a distal end side of the polygonal ring part. It is good also as a structure which has the aperture
- the throttle portion is formed in a cylindrical shape, the second gap between the outer peripheral surface of the throttle portion and the inner peripheral surface of the second cylinder is uniform. Thereby, the air ejected from the gap can be made uniform in the circumferential direction.
- the convex portion may be formed at the center in the circumferential direction of the outer peripheral plane of the polygonal ring portion.
- the convex portion is formed with a uniform thickness in the radial direction and a high-precision convex portion whose peripheral surface extends in the radial direction. Can be formed.
- the cross-sectional shape of the convex portion viewed from the radial direction along the diameter of the first cylinder may be a spindle shape along the axial direction.
- the present invention also provides a gas turbine comprising any one of the combustors described above and a turbine driven by combustion gas sent from the second cylinder of the combustor.
- the gas turbine includes the combustor, the number of parts can be reduced, and the manufacturing cost of the combustor can be reduced.
- the main body portion and the convex portion are integrally formed in the ring portion, the number of parts can be reduced and the manufacturing cost of the combustor can be reduced.
- the outer peripheral surface of the main body, which is a processing target the number of changes in the relative angle between the processing tool and the processing target is reduced, so that the number of processing steps can be reduced.
- FIG. 6 is a sectional view taken along line VI-VI in FIG. 5. It is a VII arrow line view of FIG. It is sectional drawing corresponding to FIG. 6 explaining the manufacturing method of the exit outer side ring in embodiment of this invention. It is sectional drawing explaining the manufacturing method of the exit outer side ring in a comparative example. It is sectional drawing corresponding to FIG. 6 which shows the exit outer side ring of a modification.
- the gas turbine GT of the present embodiment is rotationally driven by a compressor 1 that generates compressed air, a combustor 3 that burns fuel in compressed air to generate combustion gas, and the combustion gas.
- the turbine 5 is provided.
- the turbine 5 includes a turbine casing 6 that forms a casing 7 therein, and a turbine rotor 8 that is rotatably provided in the casing 7.
- the compressor 1 takes in external air from the air intake port 2 and compresses the air to generate compressed air.
- the combustor 3 mixes fuel with the compressed air from the compressor 1 and burns it.
- the high-temperature and high-pressure combustion gas generated by the combustion of the fuel drives the turbine rotor 8 to rotate.
- the combustor 3 supplies the compressed air A and fuel from the compressor 1 (see FIG. 1), and the compressed air A and fuel from the fuel supplier 10.
- An inner cylinder 20 first cylinder
- a tail cylinder 30 second cylinder
- Both the inner cylinder 20 and the tail cylinder 30 of the combustor 3 are disposed in the casing 7 of the turbine 5.
- the fuel supplier 10 includes a pilot burner 11 that supplies pilot fuel and compressed air A from the compressor 1, and a plurality of nozzles that premix the main fuel and compressed air A from the compressor 1 to form a premixed gas. 12.
- the inner cylinder 20 is arranged on the first direction side of the inner cylinder 20 and has a cylindrical inner cylinder body 39, and an annular shape arranged on the second direction side opposite to the first direction of the inner cylinder 20. And an outlet outer ring 40.
- a fuel supplier 10 is provided at the end in the first direction of the inner cylinder 20, and an opening 25 is formed at the end in the second direction.
- the outlet outer ring 40 forms the tip of the inner cylinder 20.
- the end portion in the first direction of the inner cylinder main body 39 is referred to as a base end portion 21, and the end portion in the second direction is referred to as a distal end portion 22.
- the base end 21 that is the end in the first direction is the upstream side
- the tip 22 that is the end in the second direction is the downstream.
- the direction along the axis O of the inner cylinder 20 will be described as the axial direction, the direction along the circumference around the axis O as the circumferential direction, and the direction along the diameter of the circumference as the radial direction.
- the outlet outer ring 40 is attached to the distal end portion 22 of the inner cylinder main body 39.
- the outlet outer ring 40 has a shape that extends the inner cylinder main body 39 so as to increase its diameter toward the downstream side.
- the tail cylinder 30 has a cylindrical shape, and an opening 35 is formed at an end in the first direction.
- the inner diameter of the opening 35 is larger than the outer diameter of the distal end portion 22 of the inner cylinder 20 and the outer diameter of the outlet outer ring 40.
- the upstream end portion of the transition piece 30 is referred to as a base end portion 31.
- the proximal end portion 31 of the tail tube 30 the distal end portion 22 of the inner tube main body portion 39 and the outlet outer ring 40 are inserted.
- the downstream end of the transition piece 30 is connected to the combustion passage of the turbine 5 (see FIG. 1).
- the fuel supplier 10 is fixed to the turbine casing 6.
- the inner cylinder 20 is supported by a fuel supplier 10 whose base end 21 is fixed to the turbine casing 6.
- the distal end portion 22 of the inner cylinder main body 39 is supported by a support member (not shown) provided in the turbine casing 6 together with the proximal end portion 31 of the tail cylinder 30.
- the pilot burner 11 and the plurality of nozzles 12 of the fuel supplier 10 are disposed inside the inner cylinder 20. Further, the combustors 3 are connected to each other via a connecting portion (not shown). The flame of the combustor 3 propagates to the adjacent combustor 3 through the connecting portion.
- a gap S ⁇ b> 1 is formed between the outer peripheral surface 20 b of the inner cylinder main body 39 and the inner peripheral surface 30 a of the tail cylinder 30 at the connection portion (fitting) between the inner cylinder 20 and the tail cylinder 30.
- the clearance S1 allows expansion and displacement of the inner cylinder 20 and the tail cylinder 30 due to heat.
- a plate spring 23 and a seal plate 24 supported by the plate spring 23 are attached to the outer peripheral surface 20b near the tip 22 of the inner cylinder main body 39 in order to seal the gap S1.
- the seal plate 24 is a cylindrical thin plate for sealing a connection portion between the inner cylinder 20 and the tail cylinder 30. A plurality of slits (not shown) are formed in the seal plate 24 at intervals in the circumferential direction.
- the seal plate 24 has an upstream outer peripheral surface in contact with the inner peripheral surface 30 a of the tail cylinder 30, and a downstream inner peripheral surface joined to the outer peripheral surface 20 b of the inner cylinder main body 39.
- the leaf spring 23 is an elastic member that urges the upstream side of the seal plate 24 from the radially inner peripheral side toward the inner peripheral surface 30 a of the tail tube 30.
- the leaf spring 23 has a cylindrical shape like the seal plate 24.
- the outlet outer ring 40 connected to the distal end portion 22 of the inner cylinder main body 39 includes a cylindrical main body 41 and a plurality of protrusions provided on the outer peripheral surface of the main body 41 in the circumferential direction and projecting radially outward. 42.
- a taper-shaped enlarged surface 43 that gradually increases in diameter toward the downstream side is formed on the inner peripheral side of the main body 41. Compressed air A and fuel are smoothly supplied from the inner cylinder 20 to the tail cylinder 30 by the enlarged surface 43.
- the main body portion 41 of the outlet outer ring 40 includes a fitting portion 44 that fits into the distal end portion 22 of the inner cylinder main body portion 39 in order from the upstream side, a polygonal ring portion 45, and a throttle. Part 46.
- the outlet outer ring 40 is formed with at least one (two in this embodiment) notch 47.
- the notch 47 is provided on the throttle portion 46 side in the axial direction.
- the notch 47 functions as a passage for the flame that propagates through the connecting pipe described above.
- the shape of the main body 41 will be described assuming that the notch 47 is not provided.
- the outlet outer ring 40 is formed with a notch 47 having a different shape depending on the position and shape of the combustor 3 to be attached.
- the notch 47 is used not only for the propagation of flame but also for the connection with the spark plug and for the detection of flame.
- the fitting portion 44 has a shape that fits with the inner peripheral surface 20a of the distal end portion 22 of the inner cylinder main body portion 39 without a gap. That is, in the outlet outer ring 40, the fitting portion 44 has an outer diameter smaller than the inner diameter of the distal end portion 22 of the inner cylinder main body portion 39.
- the outer peripheral surface 46a of the throttle part 46 is formed in a cylindrical shape.
- a gap S ⁇ b> 2 (see FIG. 3) is provided between the outer peripheral surface 46 a of the throttle unit 46 and the inner peripheral surface 30 a of the transition piece 30.
- the outer diameter of the throttle part 46 is formed with a gap S2 between the inner peripheral surface 30a of the tail cylinder 30.
- the polygonal ring portion 45 has a polygonal cross-sectional shape viewed from the axial direction. That is, the outer peripheral surface 45 a of the polygonal ring portion 45 is not formed in an arc shape, and has a plurality of outer peripheral planes 50 and a plurality of ridge lines 51 formed between the outer peripheral planes 50 and 50. ing.
- the outer peripheral surface 45a of the polygonal ring portion 45 of the present embodiment has a 32 square shape with a cross-sectional shape viewed from the axial direction having 32 planes and 32 ridge lines.
- the shape of the outer peripheral surface 45a of the polygonal ring portion 45 is not limited to this embodiment, and various polygonal shapes can be employed.
- the polygonal shape can be appropriately set according to the diameter of the inner cylinder 20 or the like. For example, if it is an inner cylinder smaller than the diameter of the inner cylinder 20 of this embodiment, it can be made into a polygonal shape with fewer planes and ridge lines than this embodiment, such as a decagon.
- the outer peripheral plane 50 is formed on the radially inner side with respect to the outer peripheral surface 46a of the throttle part 46. In other words, the distance from the central axis O of the outer peripheral plane 50 is shorter than the radius of the outer peripheral surface 46 a of the throttle portion 46. Thereby, as shown in FIG. 3, the clearance S3 between the outer peripheral plane 50 and the inner peripheral surface 30a of the transition piece 30 is larger than the clearance S2.
- the convex part 42 has the protrusion end surface 52 substantially parallel to the outer peripheral surface 45a.
- the protruding end surface 52 is formed on the outer side in the radial direction from the outer peripheral surface 46 a of the throttle portion 46. As shown in FIG. 3, the protruding end surface 52 is formed so that the height from the outer peripheral plane 50 is substantially the same as the gap S3.
- the convex part 42 is formed so as to extend in the axial direction substantially at the center in the circumferential direction of the outer peripheral plane 50.
- the cross-sectional shape of the convex portion 42 viewed from the radial direction is a spindle shape extending in the axial direction.
- the convex portion 42 has an elliptical shape in which the cross-sectional shape orthogonal to the radial direction extends in the flow direction of the compressed air A and has a shape that does not hinder the flow of the compressed air A flowing in from the upstream side as much as possible. is doing.
- a plurality of (for example, eight) air supply holes 32 are formed in the vicinity of the base end portion 31 of the transition piece 30 in the circumferential direction.
- the axial position of the air supply hole 32 is on the downstream side of the seal plate 24 and the upstream side of the convex portion 42 when the tail cylinder 30 and the inner cylinder 20 are combined.
- the air supply hole 32 is such that the compressed air A flowing in from the outer peripheral side of the tail cylinder 30 is downstream of the seal plate 24 in the gap S1 between the tail cylinder 30 and the inner cylinder 20, and upstream of the convex portion 42. It is formed at a position where it flows into.
- the exit outer ring 40 of the present embodiment is manufactured by making the outline using a machine tool such as a lathe and then machining the details using a machine tool such as a milling machine.
- a machine tool such as a lathe
- a machine tool such as a milling machine.
- the polygonal ring portion 45 of the outlet outer ring 40 is processed by an end mill of a milling machine because the convex portion 42 protruding in the radial direction is integrally formed.
- the outer peripheral flat surface 50 is processed using the end mill M so that the convex portions 42 remain. Since there are 32 outer peripheral planes 50 in this embodiment, in order to process these outer peripheral planes 50, the relative angle between the end mill M and the object to be processed is changed 32 times including the initial installation. That is, the outer peripheral flat surface 50 on which the convex portions 42 are formed is processed by changing the angle of the pitch P1 32 times.
- the compressed air A compressed by the compressor 1 is a flow path 14 () surrounded by the outer peripheral surface 30b of the tail cylinder 30, the outer peripheral surface 20b of the inner cylinder 20, and the inner peripheral surface of the turbine casing 6. 2), the flow is reversed by the reversing unit 15 and flows into the inner cylinder 20.
- fuel and compressed air A supplied from the pilot burner 11 and the plurality of nozzles 12 of the fuel supplier 10 are supplied from the inner cylinder 20 to the tail cylinder 30.
- the fuel and compressed air A supplied from the inner cylinder 20 form a flame in the tail cylinder 30.
- a diffusion flame is formed by the pilot fuel and compressed air A supplied from the pilot burner 11.
- the premixed gas generated by premixing the main fuel and the compressed air A at the plurality of nozzles 12 is ignited by the diffusion flame. Thereby, a premixed flame is formed.
- Combustion gas G generated by combustion of pilot fuel and main fuel is sent from the tail cylinder 30 into a turbine side gas flow path (not shown). As described above, the combustion gas G that has entered the turbine side gas flow path drives the turbine rotor 8 to rotate.
- the compressed air A is taken into the space between the tail cylinder 30 and the inner cylinder 20 through the air supply hole 32.
- the introduced compressed air A is ejected along the inner peripheral surface 30 a of the transition piece 30 from the gap S ⁇ b> 2 between the transition piece 30 and the throttle part 46 of the outlet outer ring 40.
- the compressed air A ejected to the transition piece 30 forms a thin film on the inner peripheral surface 30 a of the transition piece 30. That is, the film of the compressed air A cools the inner peripheral surface 30a of the tail cylinder 30, and the fuel and compressed air A supplied from the opening 25 of the inner cylinder 20 and the heat of the combustion gas G generated from them.
- the inner peripheral surface 30a of the tail cylinder 30 is protected from the above. Further, the compressed air A introduced into the transition piece 30 from the gap S1 may be used as combustion air.
- the compressed air A ejected from the gap S2 cools the tail cylinder 30 with a film, whereby the burning of the tail cylinder 30 can be suppressed.
- the convex portion 42 is formed on the outlet outer ring 40, the gap S3 for supplying the compressed air A for film cooling of the tail cylinder 30 can be stably secured. Further, since the convex portion 42 is formed integrally with the outlet outer ring 40, the number of parts for configuring the inner cylinder 20 of the combustor 3 can be reduced.
- the cross-sectional shape viewed from the radial direction of the convex portion 42 is a spindle shape along the axial direction, the disturbance of the compressed air A at the convex portion 42 placement position is effectively suppressed. Thereby, the uniformity of the compressed air A ejected from the gap S2 can be improved.
- the polygonal ring portion 45 of the outlet outer ring 40 is formed in a polygonal shape, the number of changes in the relative angle between the machining tool and the machining object can be reduced when the outer peripheral plane 50 of the polygonal ring portion 45 is formed. Less. Thereby, a processing man-hour can be reduced.
- FIG. 9 is a cross-sectional view illustrating a method for manufacturing the outlet outer ring 140 of the comparative example.
- the outlet outer ring 140 of the comparative example is formed in a cylindrical shape as viewed from the axial direction at a portion corresponding to the polygonal ring portion 45 of the present embodiment.
- the machining pitch P2 of the end mill M is about 1 °.
- the polygonal ring portion 45 of the outlet outer ring 40 of the present embodiment is formed in a polygonal shape.
- the pitch P1 is about 11 ° as shown in FIG.
- the diameter of the end mill M can be increased by making the polygonal ring portion 45 into a polygonal shape. That is, when the machining pitch is small, an end mill M having a size corresponding to the pitch is required. However, the end mill M is allowed to have a large diameter by increasing the machining pitch and the machining plane. That is, the diameter D1 of the end mill M that processes the outlet outer ring 40 of this embodiment can be made larger than the diameter D2 of the end mill M that processes the outlet outer ring 140 of the comparative example.
- the outer peripheral surface 46a of the throttle portion 46 is formed in a cylindrical shape, and the gap S2 between the outer peripheral surface 46a of the throttle portion 46 and the inner peripheral surface 30a of the transition piece 30 is uniform, the clearance S2 The compressed air A to be ejected can be made uniform in the circumferential direction.
- the convex portion 42 is formed at the center in the circumferential direction of the outer peripheral plane 50 of the polygonal ring portion 45, the end portion M for forming the outer peripheral plane 50 is used to form the convex portion 42. It is possible to form the convex portion 42 having a uniform direction and a high accuracy with the circumferential surface extending in the radial direction.
- the convex portion 42 of the outlet outer ring 40 is formed integrally with the main body portion 41, it is not necessary to form it at the center in the circumferential direction of the outer peripheral plane 50.
- the convex portion 42 ⁇ / b> B may be formed on the ridge line between the outer peripheral plane 50 and the outer peripheral plane 50.
- the introduction of the compressed air A used for film cooling is not limited to the method through the air supply hole 32, and other introduction methods may be used.
- the compressed air A may be introduced from a slit formed in the seal plate 24.
- the shape of the convex portion 42 is not limited to the shape of a spindle viewed in the radial direction, and a shape that does not affect the flow of the compressed air A can be appropriately employed. For example, it may be a circular shape in the radial direction. Further, the number of the convex portions 42 is not limited to one on the outer peripheral plane 50, and a plurality of convex portions 42 may be formed.
- the main body portion and the convex portion are integrally formed in the ring portion, the number of parts can be reduced and the manufacturing cost of the combustor can be reduced.
- the outer peripheral surface of the main body, which is a processing target the number of changes in the relative angle between the processing tool and the processing target is reduced, so that the number of processing steps can be reduced.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Pre-Mixing And Non-Premixing Gas Burner (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Nozzles For Spraying Of Liquid Fuel (AREA)
Abstract
Description
本願は、2013年3月15日に出願された特願2013-053149号について優先権を主張し、その内容をここに援用する。
スペーサーは、出口外側リングの外周面に周方向に複数取り付けられている。スペーサーが尾筒の内周面に当接することによって、フィルム空気を供給するための隙間が全周にわたって均一に確保される。
図1に示すように、本実施形態のガスタービンGTは、圧縮空気を生成する圧縮機1と、燃料を圧縮空気中で燃焼させ燃焼ガスを生成する燃焼器3と、燃焼ガスによって回転駆動されるタービン5とを備えている。タービン5は、内部に車室7を形成するタービンケーシング6と、車室7内に回転可能に設けられているタービンロータ8とを有している。
出口外側リング40は、内筒本体部39の先端部22に取り付けられている。出口外側リング40は、内筒本体部39を下流側に向かって拡径するように延長する形状である。
板バネ23は、シール板24の上流側を径方向内周側から尾筒30の内周面30aに向かって付勢する弾性部材である。板バネ23は、シール板24と同様に円筒形状をなしている。
本実施形態の出口外側リング40は、その概形を例えば旋盤などの工作機械を用いて作製した後、例えばフライス盤などの工作機械を用いて細部を加工することによって製造される。特に、出口外側リング40の多角リング部45については、径方向に突出する凸部42が一体に形成されているため、フライス盤のエンドミルによって加工される。
また、隙間S1から尾筒30に導入される圧縮空気Aは、燃焼用の空気として使用されてもよい。
また、凸部42が出口外側リング40に一体に形成されていることによって、燃焼器3の内筒20を構成するための部品点数を削減することができる。
また、凸部42の数は、外周平面50に一つに限らず、複数形成してもよい。
2 空気取込口
3 燃焼器
5 タービン
6 タービンケーシング
7 車室
8 タービンロータ
10 燃料供給器
11 パイロットバーナ
12 ノズル
20 内筒(第一筒)
20a 内周面
20b 外周面
21 基端部
22 先端部
23 板バネ
24 シール板
25 開口
30 尾筒(第二筒)
30a 内周面
30b 外周面
31 基端部
32 空気供給孔
35 開口
39 内筒本体部(第一筒本体部)
40 出口外側リング(リング部)
41 本体部
42 凸部
43 拡大面
44 嵌合部
45 多角リング部
45a 外周面
46 絞り部
46a 外周面
47 切欠部
50 外周平面
51 稜線
52 突出端面
A 圧縮空気
G 燃焼ガス
GT ガスタービン
S1 隙間
S2 隙間
S3 隙間
Claims (5)
- 先端の開口から燃料及び空気を供給する第一筒と、
前記燃料及び空気により内周側に火炎が形成され前記第一筒の先端が基端の内周側に挿入されている第二筒と、を備え、
前記第一筒は、第一筒本体部と前記第一筒の先端を形成するリング部とを備え、
前記リング部は、筒状の本体部と、前記本体部の外周面に前記本体部と一体に周方向に複数設けられ、径方向外側へ突出する凸部とを有し、
前記本体部の外周面は、前記凸部が形成される範囲で前記第一筒の軸線に沿う軸方向から視た断面形状が多角形状に形成されている燃焼器。 - 前記本体部は、前記凸部が形成された多角リング部と、前記多角リング部よりも先端側に設けられ、前記多角リング部の外周面よりも径方向外周側に外周面が円筒状に形成された絞り部と、を有する請求項1に記載の燃焼器。
- 前記凸部は、前記多角リング部の外周平面の周方向中央に形成されている請求項2に記載の燃焼器。
- 前記第一筒の径に沿う径方向から視た前記凸部の断面形状が軸方向沿った紡錘形状とされている請求項1から請求項3のいずれか一項に記載の燃焼器。
- 請求項1から請求項4のいずれか一項に記載の燃焼器と、
前記燃焼器の前記第二筒から送出された燃焼ガスにより駆動するタービンと、を備えているガスタービン。
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CN201480010620.1A CN105008696B (zh) | 2013-03-15 | 2014-02-18 | 燃烧器以及燃气轮机 |
US14/770,638 US9939158B2 (en) | 2013-03-15 | 2014-02-18 | Combustor with ring part having protrusions and gas turbine including the combustor |
KR1020157023033A KR101716602B1 (ko) | 2013-03-15 | 2014-02-18 | 연소기 및 가스 터빈 |
EP14762567.7A EP2949904B1 (en) | 2013-03-15 | 2014-02-18 | Combustor and gas turbine |
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JP2013053149A JP6082287B2 (ja) | 2013-03-15 | 2013-03-15 | 燃焼器、ガスタービン、及び燃焼器の第一筒 |
JP2013-053149 | 2013-03-15 |
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US (1) | US9939158B2 (ja) |
EP (1) | EP2949904B1 (ja) |
JP (1) | JP6082287B2 (ja) |
KR (1) | KR101716602B1 (ja) |
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WO2016047601A1 (ja) * | 2014-09-25 | 2016-03-31 | 三菱日立パワーシステムズ株式会社 | 燃焼器、ガスタービン |
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US20170142395A1 (en) * | 2015-11-13 | 2017-05-18 | Craig Peterson | 3d system including pop out adjustment |
CN109154440B (zh) * | 2016-05-23 | 2021-03-23 | 三菱动力株式会社 | 燃烧器、燃气轮机 |
JP6590771B2 (ja) | 2016-08-09 | 2019-10-16 | 三菱日立パワーシステムズ株式会社 | ガスタービン燃焼器 |
JP6779098B2 (ja) * | 2016-10-24 | 2020-11-04 | 三菱パワー株式会社 | ガスタービン燃焼器 |
US12055299B2 (en) * | 2020-02-19 | 2024-08-06 | Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. | Combustor and gas turbine |
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- 2014-02-18 CN CN201480010620.1A patent/CN105008696B/zh active Active
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CN107076419A (zh) * | 2014-09-25 | 2017-08-18 | 三菱日立电力系统株式会社 | 燃烧器、燃气轮机 |
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KR101889671B1 (ko) * | 2014-09-25 | 2018-08-17 | 미츠비시 히타치 파워 시스템즈 가부시키가이샤 | 연소기, 가스 터빈 |
CN107076419B (zh) * | 2014-09-25 | 2019-09-06 | 三菱日立电力系统株式会社 | 燃烧器、燃气轮机 |
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Also Published As
Publication number | Publication date |
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US20160003481A1 (en) | 2016-01-07 |
KR101716602B1 (ko) | 2017-03-14 |
CN105008696B (zh) | 2017-10-03 |
US9939158B2 (en) | 2018-04-10 |
JP6082287B2 (ja) | 2017-02-15 |
EP2949904B1 (en) | 2017-08-02 |
EP2949904A1 (en) | 2015-12-02 |
CN105008696A (zh) | 2015-10-28 |
KR20150110757A (ko) | 2015-10-02 |
JP2014177909A (ja) | 2014-09-25 |
EP2949904A4 (en) | 2016-04-20 |
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