WO2013077394A1 - 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
- WO2013077394A1 WO2013077394A1 PCT/JP2012/080278 JP2012080278W WO2013077394A1 WO 2013077394 A1 WO2013077394 A1 WO 2013077394A1 JP 2012080278 W JP2012080278 W JP 2012080278W WO 2013077394 A1 WO2013077394 A1 WO 2013077394A1
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- WIPO (PCT)
- Prior art keywords
- combustion cylinder
- hole
- combustion
- circumferential direction
- peripheral surface
- 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
- F23R3/002—Wall structures
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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
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/06—Arrangement of apertures along the flame tube
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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
- 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
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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
- F23R2900/00014—Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators
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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
- F23R2900/03042—Film cooled combustion chamber walls or domes
Definitions
- the present invention relates to a combustor for a gas turbine, and more particularly to wall cooling of the combustor.
- cooling is performed by a cooling groove provided inside the wall surface of the combustion cylinder to suppress the temperature rise of the wall surface.
- Patent Document 1 discloses an acoustic liner that is provided on the outer peripheral surface of a combustion cylinder and attenuates combustion vibration. Then, as a technique for preventing the above-mentioned wall surface combustion by suppressing the temperature rise of the wall surface, it is considered that purge air is supplied to the acoustic hole of this acoustic liner to form film air on the wall surface of the combustion cylinder. It is done.
- the present invention has been made in consideration of such circumstances, and provides a combustor and a gas turbine capable of preventing the occurrence of wall surface combustion by forming circumferentially continuous film air on the inner peripheral surface of a combustion cylinder.
- the purpose is to do.
- the present invention employs the following means. That is, the gas turbine combustor according to the present invention is an acoustic liner provided between the combustion cylinder that forms the combustion space inside and the outer peripheral surface of the combustion cylinder that defines the acoustic space.
- a through hole group is formed in the combustion cylinder to communicate the combustion space and the acoustic space, and the through hole group has a plurality of through hole arrays arranged at intervals in the circumferential direction.
- a plurality of adjacent through-hole rows in the row of adjacent through-holes are arranged so as to overlap each other in the circumferential direction with their respective central axes shifted in the circumferential direction.
- a cooling groove is formed inside the combustion cylinder corresponding to a position where the acoustic liner is provided, so as to avoid the through hole. Is a transverse cooling that extends in the circumferential direction between the through-hole rows. And the groove extends in the axial direction between the through-holes with each other, characterized in that it has a longitudinal cooling grooves connecting the transverse cooling grooves adjacent to each other in the axial direction.
- the through holes are arranged so as to overlap each other in the circumferential direction, and when purge air is introduced from the through holes into the combustion cylinder, the film air continuous in the circumferential direction is formed. It is formed on the wall surface inside the combustion cylinder.
- Such a continuous film air in the circumferential direction suppresses the temperature rise in the entire circumferential direction of the combustion cylinder, increases the mixing ratio of air to the fuel near the inner peripheral surface of the combustion cylinder, and reduces the fuel concentration. it can.
- the cooling cylinders can be cooled without interfering with the through holes, and the temperature of the combustion cylinder can be cooled.
- the upstream hole diameter of the through hole may be larger than the downstream side in the axial direction.
- the through hole may be inclined inward in the radial direction of the combustion cylinder from the upstream side in the axial direction toward the downstream side.
- Such a through-hole makes it possible to supply the purge air to a position closer to the inner peripheral surface of the combustion cylinder, to form film air more reliably, and to further improve the effect of preventing wall surface combustion.
- At least one of the through hole may have an enlarged diameter among an opening on the outer peripheral surface of the combustion cylinder and an opening on the inner peripheral surface of the combustion cylinder.
- the purge air can be smoothly taken in, and the purge air can be supplied so as to spread over the inner peripheral surface of the combustion cylinder. It can be improved.
- a gas turbine combustor according to the present invention is an acoustic liner provided between the combustion cylinder that forms a combustion space inside and the outer peripheral surface of the combustion cylinder that defines an acoustic space.
- a through hole group is formed in the combustion cylinder to communicate the combustion space and the acoustic space, and the through hole group has a plurality of through hole arrays arranged at intervals in the circumferential direction.
- a plurality of adjacent through-hole rows of the through-hole rows adjacent to each other are arranged with their respective central axes aligned in the circumferential direction, and the circumferential direction of the through-holes
- An auxiliary through-hole that connects the cooling groove and the combustion space is formed in a cooling groove formed inside between the outer peripheral surface and the inner peripheral surface of the combustion cylinder.
- a gas turbine according to the present invention includes the combustor.
- continuous film air in the circumferential direction can be formed on the inner peripheral surface of the combustion cylinder of the combustor, and the occurrence of wall surface combustion can be prevented.
- continuous film air in the circumferential direction can be formed on the inner peripheral surface of the combustion cylinder, and wall surface combustion can be prevented.
- FIG. 1 is an overall schematic diagram of a gas turbine according to a first embodiment of the present invention. It is the whole combustor schematic diagram in the gas turbine concerning a first embodiment of the present invention. It is a perspective view which shows the acoustic liner of a combustor regarding the gas turbine which concerns on 1st embodiment of this invention.
- FIG. 3 is a view showing a positional relationship between a through hole and a cooling groove in an acoustic liner of a combustor relating to the gas turbine according to the first embodiment of the present invention, and is a view of FIG. 3 viewed from the inner peripheral surface side of the combustion cylinder. .
- the gas turbine 1 which concerns on embodiment of this invention is demonstrated.
- the gas turbine 1 is combusted after the compressed air A generated in the compressor 2 is mixed with the fuel F in the combustor (gas turbine combustor) 3, and the high-temperature / high-pressure combustion gas G Is configured to generate
- the combustion gas G flows into the turbine 4 to rotate the rotor 5 of the turbine 4 to obtain rotational power.
- the combustion gas G is exhausted after the turbine 4 is rotated. It is exhausted through the chamber 6.
- the compressor 2 side (left side in FIG. 1) of the gas turbine 1 is referred to as the upstream side
- the exhaust chamber 6 side (right side in FIG. 1) is referred to as the downstream side.
- the combustor 3 is connected to the fuel supply unit 10 that supplies the fuel F and the compressed air A from the compressor 2, a combustion cylinder 11 that burns these to generate a high-temperature / high-pressure combustion gas G, and the combustion cylinder 11. And the acoustic part 13 provided outside the combustion cylinder 11.
- the fuel supplier 10 supplies a premixed gas FA in which the fuel F and the compressed air A are premixed into the combustion cylinder 11 and burns the premixed gas FA.
- the combustion cylinder 11 has a substantially cylindrical shape centered on the axis P, and is connected to the fuel supply device 10 on the upstream side to generate the combustion gas G in the internal combustion space.
- the downstream side is connected to the transition piece 12 so that the combustion gas G can flow into the turbine 4 via the transition piece 12.
- the tail cylinder 12 is a substantially cylindrical member connected to the combustion cylinder 11 on the upstream side and connected to the turbine 4 on the downstream side, and the combustion gas G generated in the combustion cylinder 11 is transferred to the turbine 4. To supply.
- the acoustic unit 13 includes an acoustic liner 15 provided on the outer peripheral surface of the combustion cylinder 11, and a through hole group formed by communicating the inside and outside of the combustion cylinder 11 at the installation position of the acoustic liner 15. 16 and a cooling groove 17 formed inside the combustion cylinder 11 between the outer peripheral surface and the inner peripheral surface at the installation position of the acoustic liner 15.
- the acoustic liner 15 is a ring-shaped member provided around the outer peripheral surface of the combustion cylinder 11 in the circumferential direction.
- the acoustic liner 15 is provided so as to define a space (acoustic space) S with the outer peripheral surface so as to cover the outer peripheral surface of the combustion cylinder 11 from the radially outer side.
- the through-hole group 16 is a plurality of through-holes 16 a formed so as to communicate with the inside and outside of the combustion cylinder 11 at the installation position of the acoustic liner 15, and purge air PA is formed from the outside to the inside of the combustion cylinder 11. Is introduced. Further, in the through hole group 16, the through holes 16 a arranged at intervals in the circumferential direction of the combustion cylinder 11 constitute a through hole row 16 b, and the through hole row 16 b is spaced in the axis P direction. There are multiple arrays.
- each through-hole 16a may overlap with the circumferential direction in the state which center axis
- the state which overlaps with the circumferential direction includes the state where the outer periphery of the through-hole 16a contact
- the cooling groove 17 is a flow path that is formed inside the outer peripheral surface and the inner peripheral surface of the combustion cylinder 11 at the installation position of the acoustic liner 15 and allows the cooling air CA to flow therethrough. is there.
- the cooling groove 17 is formed to be inclined from the upstream side in the axis P direction toward the downstream side and from one side in the circumferential direction toward the other side so as to avoid the installation position of the through hole 16a.
- the cooling groove 17 is continuously formed inside the outer peripheral surface and the inner peripheral surface of the combustion cylinder 11 at positions other than the position where the through-hole group 16 is formed. Since it is not necessary to form the cooling groove 17 at a position other than the position, the cooling groove 17 is formed in parallel to the axis P direction in this embodiment.
- the purge from the through holes 16 a adjacent in the circumferential direction is performed.
- the working air PA flows into the combustion cylinder 11 from the through hole 16a so as to overlap in the circumferential direction. That is, since the purge air PA is continuous in the circumferential direction, film air that is continuous in the circumferential direction is formed on the inner peripheral surface of the combustion cylinder 11. By such film air continuous in the circumferential direction, the entire combustion cylinder 11 can be cooled without leakage, and the temperature rise of the combustion cylinder 11 can be suppressed. Further, such film air can increase the air mixing ratio to the fuel F in the vicinity of the inner peripheral surface of the combustion cylinder 11 and can reduce the concentration of the fuel F, so that the occurrence of wall surface combustion can be prevented.
- the cooling groove 17 is formed to be inclined with respect to the direction of the axis P, so that the cooling groove 17 can be provided without interfering with the through hole 16a, and the purge air PA is used.
- the cooling groove 17 does not have a complicated structure because it is formed to be inclined, the combustion cylinder 11 can be reliably cooled while maintaining the durability of the combustion cylinder 11, and the temperature rise of the combustion cylinder 11 is suppressed. It is possible to improve the effect of preventing wall surface combustion.
- the temperature increase of the inner peripheral surface of the combustion cylinder 11 can be suppressed by the film air continuous in the circumferential direction, and further, the effect of suppressing the temperature increase can be improved by the cooling groove 17. Further, since the concentration of the fuel F can be reduced by the film air, it is possible to reliably prevent the occurrence of wall surface combustion.
- the gas turbine 1 according to the second embodiment will be described.
- symbol is attached
- the acoustic unit 23 is replaced with the cooling groove 17 of the first embodiment, and the cooling groove 27 has a horizontal cooling groove 27 a and a vertical cooling groove 27 b. .
- the horizontal cooling groove 27a is formed inside the outer peripheral surface and the inner peripheral surface of the combustion cylinder 11 at the installation position of the acoustic liner 15, and serves as a flow path through which the cooling air CA can flow.
- the lateral cooling groove 27a extends in the circumferential direction between the through-hole rows 16b adjacent in the axis P direction so as to avoid the installation position of the through-hole 16a.
- the vertical cooling groove 27b is formed in the inside sandwiched between the outer peripheral surface and the inner peripheral surface of the combustion cylinder 11 at the installation position of the acoustic liner 15 and allows the cooling air CA to flow in the same manner as the horizontal cooling groove 27a.
- the horizontal cooling grooves 27a that extend in the axis P direction between the adjacent through holes 16a in the circumferential direction are connected to each other.
- the vertical cooling grooves 27b are alternately arranged in the circumferential direction with respect to the direction of the axis P.
- cooling grooves are formed in the combustion cylinder 11 other than the formation position of the through-hole group 16 so as to be continuous with the horizontal cooling grooves 27a and the vertical cooling grooves 27b. Need not have the horizontal cooling grooves 27a and the vertical cooling grooves 27b.
- the cooling groove 27 can be provided by the horizontal cooling groove 27a and the vertical cooling groove 27b without interfering with the through hole 16a, and the cooling air CA flows from the horizontal cooling groove 27a to the vertical cooling groove 27b. To do. At this time, it is possible to improve the cooling effect of the combustion cylinder 11 by improving the heat transfer efficiency by boundary layer separation, to reliably cool the combustion cylinder 11 to suppress the temperature rise, and to improve the effect of preventing the occurrence of wall surface combustion. Can do.
- the temperature rise of the combustion cylinder 11 can be suppressed by the film air continuous in the circumferential direction, and further, the effect of suppressing the temperature rise by the horizontal cooling groove 27a and the vertical cooling groove 27b. It can be improved. Further, since the fuel F concentration can be reduced by the film air, it is possible to reliably prevent the occurrence of wall surface combustion.
- gas turbine 1 according to the third embodiment will be described.
- symbol is attached
- the gas turbine 1 of the present embodiment is different from the first embodiment and the second embodiment in the through hole 36a in the acoustic part 33.
- the through hole 36 a has a larger hole diameter on the upstream side than the downstream side in the direction of the axis P.
- the upstream side inside the combustion cylinder 11 is more likely to cause wall surface combustion because the concentration of the fuel F is higher than the downstream side.
- the diameter of the upstream through hole 36a it becomes possible to allow more purge air PA to flow into the combustion cylinder 11 and increase the amount of film air formed on the upstream side. Can do. Therefore, it is possible to further improve the effect of preventing wall surface combustion.
- the film air continuous in the circumferential direction can suppress the temperature rise of the combustion cylinder 11 and reduce the concentration of the fuel F, and is formed on the upstream side.
- By strengthening the film air it is possible to reliably prevent the occurrence of wall surface combustion.
- the cooling groove formed inside the outer peripheral surface and the inner peripheral surface of the combustion cylinder 11 of the present embodiment may be the cooling groove 17 described in the first embodiment, or the second embodiment.
- the horizontal cooling groove 27a and the vertical cooling groove 27b may be used.
- gas turbine 1 according to the fourth embodiment will be described.
- symbol is attached
- the gas turbine 1 of the present embodiment is different from the first embodiment to the third embodiment in the through hole 46a of the acoustic unit 43.
- the through hole 46a is formed so as to be inclined inward in the radial direction of the axis P from the upstream side in the axis P direction toward the downstream side.
- the diameter increases toward the both sides in the circumferential direction toward the downstream side in the axis P direction, and on the outer peripheral surface, toward the both sides in the circumferential direction toward the upstream side in the axis P direction. It is formed to expand the diameter. That is, when the opening 48 of the through hole 46a is viewed from the radial direction, it has a substantially triangular shape.
- the occurrence of wall surface combustion can be prevented by forming film air that is continuous in the circumferential direction.
- the through hole 46a is formed to be inclined, and at least one opening 48 on the inner peripheral side and the outer peripheral side is enlarged in diameter, so that the purge air PA can be smoothly taken into the through hole 46a and burned more. It can be made to flow out so as to spread on the inner peripheral surface to a position close to the inner peripheral surface of the cylinder 11. Accordingly, the amount of film air can be increased to further strengthen the film air, and further wall surface combustion can be prevented.
- the film air continuous in the circumferential direction can be strengthened, the temperature rise of the combustion cylinder 11 can be suppressed, and the concentration of the fuel F can be reduced, thereby further reliably preventing the occurrence of wall surface combustion. it can.
- the through-hole 46a may be formed as a simple inclined hole without forming the opening 48 of the through-hole 46a with a diameter increased.
- the diameter of the opening 48 is increased by machining or the like. Time and effort can be reduced and costs can be reduced.
- the gas turbine 1 which concerns on 5th embodiment is demonstrated.
- symbol is attached
- the gas turbine 1 of the present embodiment differs from the first to fourth embodiments in the arrangement of the through-hole groups 56 of the acoustic part 53 and the arrangement of the cooling grooves 57, and between the through-holes 56a.
- An auxiliary through hole 59 is formed in the upper surface.
- the acoustic unit 53 includes an acoustic liner 15 provided on the outer peripheral surface of the combustion cylinder 11, and a through hole group formed by communicating the inside and outside of the combustion cylinder 11 at the installation position of the acoustic liner 15.
- a cooling groove 57 provided inside the outer peripheral surface and the inner peripheral surface of the combustion cylinder 11 at the installation position of the acoustic liner 15, and auxiliary through holes 59 formed between the through holes 56a.
- the through-hole group 56 is a plurality of through-holes 56 a formed so as to communicate with the inside and outside of the combustion cylinder 11 at the installation position of the acoustic liner 15, and purge air PA is formed from the outside to the inside of the combustion cylinder 11. Is introduced.
- the through holes 56a arranged at intervals in the circumferential direction of the combustion cylinder 11 constitute a through hole row 56b, and the through hole row 56b is spaced in the axis P direction. Are arranged.
- the through-hole row 56b arranged in the axial direction is arranged in a state where the central axes of the through-holes 56a adjacent in the axis P direction coincide with each other in the circumferential direction.
- the cooling groove 57 is formed inside the outer circumferential surface and the inner circumferential surface of the combustion cylinder 11 at the installation position of the acoustic liner 15, and serves as a flow path through which the cooling air CA can flow.
- the cooling groove 57 is formed from the upstream side in the axis P direction to the downstream side between the through holes 56a adjacent in the circumferential direction so as to avoid the installation position of the through hole 56a.
- the auxiliary through hole 59 is a flow passage formed in the radial direction so as to communicate with the cooling groove 57 so that the cooling groove 57 and the inside of the combustion cylinder 11 communicate with each other, and is a part of the cooling air CA that flows through the cooling groove 57.
- the portion can be discharged to the inner peripheral surface of the combustion cylinder 11.
- the structure of the cooling groove 57 can be simplified, the film air continuous in the circumferential direction can be formed while suppressing the cost, the temperature rise of the combustion cylinder 11 and the concentration of the fuel F can be suppressed. Can be achieved, and wall surface combustion can be reliably prevented from occurring.
- cooling grooves 57 parallel to the circumferential direction are formed between adjacent through-hole rows 56 b, and auxiliary through-holes 59 are formed between the adjacent through-holes 56 a in the circumferential direction.
- Two may be formed. In this case, film air continuous in the circumferential direction can be formed more reliably, and an improvement in the effect of preventing wall surface combustion can be achieved.
- the configuration of the cooling groove 57 is not limited to the above-described embodiment, and it is sufficient that the cooling groove 57 can be formed so as not to interfere with the through hole 16a.
- the cooling groove 57 may be formed from one side in the circumferential direction toward the axis P direction. You may comprise mesh shape by what is formed to the side and what is formed from the other side of the circumferential direction to one side.
- the present invention relates to a combustor and a gas turbine in which film air continuous in the circumferential direction is formed on the inner peripheral surface of a combustion cylinder and wall surface combustion can be prevented.
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Abstract
Description
本願は、2011年11月22日に日本に出願された特願2011-254979号について優先権を主張し、その内容をここに援用する。
即ち、本発明に係るガスタービン燃焼器は、内側に燃焼空間を形成する燃焼筒と、前記燃焼筒の外側に設けられ、該燃焼筒の外周面との間で音響空間を画成する音響ライナとを備え、前記燃焼筒に、前記燃焼空間と前記音響空間とを連通する貫通孔群が形成され、前記貫通孔群は、周方向に間隔をあけて配列された複数の貫通孔列が軸方向に間隔をあけて複数配列されて構成され、隣り合う前記貫通孔列の各貫通孔同士が、それぞれの中心軸同士が周方向にずれた状態で、前記周方向に互いに重なるように配置されており、前記音響ライナが設けられる位置に対応する前記燃焼筒の外周面と内周面とに挟まれる内部には、前記貫通孔を避けるように、冷却溝が形成されており、前記冷却溝は、前記貫通孔列同士の間で前記周方向に延びる横冷却溝と、前記貫通孔同士の間で前記軸方向に延びて、前記軸方向に隣り合う前記横冷却溝同士を接続する縦冷却溝とを有していることを特徴とする。
また、このような冷却溝によって、貫通孔が周方向に重なるように配置された場合であっても、貫通孔に干渉することなく冷却溝を設けて、燃焼筒を冷却でき、燃焼筒の温度上昇を抑えて、壁面燃焼の発生防止効果の向上が可能となる。
さらに、縦冷却溝が軸方向に対して周方向に互い違いに配置され、貫通孔が周方向に重なるように配置された場合であっても、貫通孔に干渉することなく、横冷却溝及び縦冷却溝を設けることができる。また、冷却空気は、横冷却溝から縦冷却溝へ分岐して流通するため、境界層剥離による熱伝達効率向上によって燃焼筒の冷却効果を向上でき、壁面燃焼の発生防止効果の向上が可能となる。
図1に示すように、ガスタービン1は、圧縮機2において生成された圧縮空気Aを、燃焼器(ガスタービン燃焼器)3で燃料Fと混合した後に燃焼し、高温・高圧の燃焼ガスGを生成するように構成されている。そしてこの燃焼ガスGをタービン4へ流入させることによって、このタービン4のロータ5を回転させ、回転動力を得るようになっており、また、上記燃焼ガスGはタービン4を回転させた後に、排気室6を通じて排気される。
なお、以下では、ガスタービン1の圧縮機2側(図1の紙面左側)を上流側と称し、排気室6側(図1の紙面右側)を下流側と称する。
燃焼器3は、燃料F及び圧縮機2からの圧縮空気Aを供給する燃料供給器10と、これらを燃焼して高温・高圧の燃焼ガスGを生成する燃焼筒11と、燃焼筒11に接続される尾筒12と、燃焼筒11の外側に設けられる音響部13とを備えている。
なお、この冷却溝17は、貫通孔群16の形成位置以外においても、燃焼筒11の外周面と内周面との間の内部に連続して形成されており、この貫通孔群16の形成位置以外の位置においては、冷却溝17を傾斜して形成する必要はないため、本実施形態では軸線P方向に平行に形成されている。
なお、第一実施形態と同様の構成要素には同一の符号を付して詳細説明を省略する。
図5に示すように、本実施形態のガスタービン1は、音響部23が第一実施形態の冷却溝17に代えて、冷却溝27が横冷却溝27a及び縦冷却溝27bを有している。
なお、第一実施形態及び第二実施形態と同様の構成要素には同一の符号を付して詳細説明を省略する。
本実施形態のガスタービン1は、第一実施形態及び第二実施形態とは、音響部33における貫通孔36aが異なっている。
なお、第一実施形態から第三実施形態と同様の構成要素には同一の符号を付して詳細説明を省略する。
本実施形態のガスタービン1は、第一実施形態から第三実施形態とは、音響部43の貫通孔46aが異なっている。
なお、第一実施形態から第四実施形態と同様の構成要素には同一の符号を付して詳細説明を省略する。
本実施形態のガスタービン1は、第一実施形態から第四実施形態とは音響部53の貫通孔群56の配置、及び冷却溝57の配置が異なっており、さらに各貫通孔56a同士の間に補助貫通孔59が形成されている。
例えば、冷却溝57の構成は上述の実施形態に限定されることなく、貫通孔16aに干渉しないように冷却溝57を形成できればよく、例えば、軸線P方向に向かって周方向の一方側から他方側へ形成されるものと、周方向の他方側から一方側へ形成されるものとによって、網目状に構成されてもよい。
2…圧縮機
3…燃焼器(ガスタービン燃焼器)
4…タービン
5…ロータ
6…排気室
A…圧縮空気
F…燃料
G…燃焼ガス
FA…予混合気体
10…燃料供給器
11…燃焼筒
12…尾筒
13…音響部
15…音響ライナ
16…貫通孔群
16a…貫通孔
16b…貫通孔列
17…冷却溝
P…軸線
S…空間(音響空間)
CA…冷却空気
PA…パージ用空気
23…音響部
27…冷却溝
27a…横冷却溝
27b…縦冷却溝
33…音響部
36a…貫通孔
46a…貫通孔
48…開口部
56…貫通孔群
56a…貫通孔
56b…貫通孔列
57…冷却溝
59…補助貫通孔
Claims (6)
- 内側に燃焼空間を形成する燃焼筒と、
前記燃焼筒の外側に設けられ、該燃焼筒の外周面との間で音響空間を画成する音響ライナとを備え、
前記燃焼筒に、前記燃焼空間と前記音響空間とを連通する貫通孔群が形成され、
前記貫通孔群は、周方向に間隔をあけて配列された複数の貫通孔列が軸方向に間隔をあけて複数配列されて構成され、
隣り合う前記貫通孔列の各貫通孔同士が、それぞれの中心軸同士が周方向にずれた状態で、前記周方向に互いに重なるように配置されており、
前記音響ライナが設けられる位置に対応する前記燃焼筒の外周面と内周面とに挟まれる内部には、前記貫通孔を避けるように、冷却溝が形成されており、
前記冷却溝は、前記貫通孔列同士の間で前記周方向に延びる横冷却溝と、
前記貫通孔同士の間で前記軸方向に延びて、前記軸方向に隣り合う前記横冷却溝同士を接続する縦冷却溝とを有していることを特徴とするガスタービン燃焼器。 - 前記貫通孔は、前記軸方向の下流側に比べて上流側の孔径が大きくなっていることを特徴とする請求項1に記載のガスタービン燃焼器。
- 前記貫通孔は、前記軸方向の上流側から下流側に向かうに従って前記燃焼筒の径方向内側に向かって傾斜していることを特徴とする請求項1又は2に記載のガスタービン燃焼器。
- 前記貫通孔は、前記燃焼筒の外周面の開口と、前記燃焼筒の内周面の開口とのうち少なくとも一方が拡径していることを特徴とする請求項1から3のいずれか一項に記載のガスタービン燃焼器。
- 内側に燃焼空間を形成する燃焼筒と、
前記燃焼筒の外側に設けられ、該燃焼筒の外周面との間で音響空間を画成する音響ライナとを備え、
前記燃焼筒に、前記燃焼空間と前記音響空間とを連通する貫通孔群が形成され、
前記貫通孔群は、周方向に間隔をあけて配列された複数の貫通孔列が軸方向に間隔をあけて複数配列されて構成され、
隣り合う前記貫通孔列の各貫通孔同士が、それぞれの中心軸同士が周方向に一致した状態で配置され、
前記貫通孔同士の前記周方向の間において前記燃焼筒の外周面と内周面とに挟まれる内部に形成される冷却溝に、該冷却溝と前記燃焼空間とを連通する補助貫通孔が形成されていることを特徴とするガスタービン燃焼器。 - 請求項1から5のいずれか一項に記載の燃焼器を備えることを特徴とするガスタービン。
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CN104040260B (zh) | 2016-01-13 |
KR101621634B1 (ko) | 2016-05-16 |
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JP5868998B2 (ja) | 2016-02-24 |
EP2784394B1 (en) | 2019-07-24 |
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CN104040260A (zh) | 2014-09-10 |
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