CN103782103B

CN103782103B - Gas turbine

Info

Publication number: CN103782103B
Application number: CN201280043745.5A
Authority: CN
Inventors: 坂元康朗; 松山敬介; 塚越敬三; 由里雅则; 岸田宏明; 鸟井俊介
Original assignee: Mitsubishi Hitachi Power Systems Ltd
Current assignee: Mitsubishi Power Ltd
Priority date: 2011-09-16
Filing date: 2012-09-12
Publication date: 2015-12-23
Anticipated expiration: 2032-09-12
Also published as: JP2013064535A; WO2013039095A1; JP5848074B2; EP2752622A1; US20140216055A1; CN103782103A; EP2752622A4

Abstract

In gas turbine of the present invention, at the downstream portion of the tail pipe of burner, the inner surface of pair of sidewalls opposite each other in the circumference of turbine rotor becomes inclined plane, this inclined plane to gradually near the direction of the tail pipe of other adjacent burners, tilts to the downstream arriving tail pipe along with the downstream of the axis direction towards tail pipe.

Description

Gas turbine

Technical field

The present invention relates to a kind of gas turbine, possess and mixed with compressed air by fuel and make fuel combustion and generate multiple burner of burning gases and have the turbine utilizing the burning gases from multiple burner to carry out the rotor rotated, the present invention especially relates to the tail pipe of burner.

The application requires priority based on No. 2011-203016, the Patent of filing an application to Japan on September 16th, 2011, here cites its content.

Background technology

Gas turbine possesses to be introduced extraneous air and generates compressed-air actuated compressor, mixed by fuel and make fuel combustion and generate multiple burner of burning gases and have the turbine utilizing the burning gases from multiple burner to carry out the rotor rotated with compressed air.Multiple burner configures in the form of a ring centered by rotor.Each burner has the tail pipe for carrying burning gases in the gas access of turbine.

When burning gases flow out from the tail pipe of burner, enter in the burning gases stream of turbine from the gas access of turbine.Now, likely burning gases are after just having flowed out from tail pipe, form toll bar vortex row among its flowing, arrange as the astable pressure oscillation of vibration source and sound equipment eigenvalue resonate, produce larger pressure oscillation, become operating load with this toll bar vortex.

Therefore, in the technology described in following patent document 1, be limited to by the size etc. in the circumference between the center between the upstream extremity by the size of the axis direction between the downstream of tail pipe and the upstream extremity of first stage stator blades sheet, first stage stator blades sheet and the tail pipe adjacent in the circumferential centered by rotor the scope determined, suppress larger pressure oscillation.

At first technical literature

Patent document

Patent document 1: Japanese Unexamined Patent Publication 2009-197650 publication

Summary of the invention

The problem that invention will solve

Technology described in above-mentioned patent document 1 reliably can suppress the larger pressure oscillation of the downstream side portion office of tail pipe.But, expect the pressure oscillation of the downstream side portion office suppressing tail pipe further, improve gas turbine proficiency further.

Therefore, the present invention is in order to tackle above-mentioned urgent expectation, and object is to provide a kind of gas turbine, can suppress the pressure oscillation of the downstream side portion office of the tail pipe of burner further, improve gas turbine proficiency further.

For solving the means of problem

(1) gas turbine of the first technical scheme of the present invention possesses: mixed with compressed air by fuel and this fuel combustion generate multiple burners of burning gases, there is the turbine utilizing the burning gases from multiple described burner to carry out the rotor rotated, multiple described burner configures in the form of a ring centered by described rotor, and there is the tail pipe of the gas access conveying burning gases to described turbine, in described gas turbine, form the downstream portion of the described tail pipe of described burner and the inner surface of the sidewall of at least one party in pair of sidewalls opposite each other in the circumference of described rotor becomes inclined plane, this inclined plane is along with the downstream of the axis direction towards described tail pipe, and to gradually near the direction of the tail pipe of other adjacent burners, tilt to the downstream arriving described tail pipe.

The burning gases flowed towards downstream in tail pipe, also flowing to the direction of the side wall inner surfaces along tail pipe after flowing out in tail pipe, therefore form toll bar vortex row in the downstream of the downstream end face of tail pipe.

In this gas turbine, the side wall inner surfaces in the downstream of tail pipe becomes the inclined plane of the downstream arriving tail pipe, therefore along the flowing of the side wall inner surfaces of the tail pipe of burner adjacent to each other each other with collaborating in the downstream of the downstream end face of tail pipe angularly, therefore, it is possible to suppress the situation forming toll bar vortex row in the downstream of the downstream end face of tail pipe, the pressure oscillation of the downstream part of tail pipe can be suppressed.

(2) in the gas turbine of above-mentioned (1), can be, described turbine has the multiple first stage stator blades sheets configured in the form of a ring and along described gas access centered by described rotor, the chord of blade direction of the chord of blade extension of described first stage stator blades sheet is relative to described peripheral, oblique, in the circumferential direction, when the side that the downstream of this first stage stator blades sheet exists being set to blade lean side at the upstream extremity relative to described first stage stator blades sheet, the sidewall of the described at least one party of described tail pipe is the sidewall of the blade lean side in sidewall described in a pair opposite each other in the circumferential in described tail pipe.

When the side wall inner surfaces of the only blade lean side in the pair of sidewalls opposite each other in the circumferential in tail pipe is inclined plane, the flowing of the burning gases guided by this inclined plane towards with the flowing of the burning gases guided by first stage stator blades sheet towards almost identical, become smooth and easy from tail pipe towards the flowing of the burning gases of first stage stator blades sheet.Therefore, even if only the inner surface of the sidewall of blade lean side is inclined plane, the pressure oscillation of the downstream part of tail pipe can also effectively be suppressed.It should be noted that, chord of blade refers to the line segment upstream extremity of stator blade and downstream linked.

In the gas turbine of (3) above-mentioned (1), Ke Yishi, described in a pair opposite each other in the circumferential in described tail pipe, the described inner surface of sidewall both sides becomes described inclined plane.

In this gas turbine, the downstream of each downstream end face of the tail pipe be connected respectively at the inner surface of the pair of sidewalls from tail pipe can be suppressed to form the situation of toll bar vortex row.

(4) in above-mentioned (1) to (3) in arbitrary gas turbine, can be, with described inclined plane from upstream extremity to downstream till the size B of circumference for benchmark, described inclined plane be more than 1 and less than 8 from the size A of axis direction of described upstream extremity to described downstream and the ratio A/B of this size B.

(5) in above-mentioned (1) to (4) in arbitrary gas turbine, Ke Yishi, described inclined plane comprises curved surface at least partially, this curved surface near the axis of described tail pipe and the side towards downstream bloat.

(6) in above-mentioned (1) to (5) in arbitrary gas turbine, can be, the quantity of described burner is the odd number of more than 2:3 with the ratio of the quantity of described first stage stator blades sheet, with the spacing dimension P of multiple described first stage stator blades sheet for benchmark, be less than 0.05,0.2 ~ 0.55 or between 0.7 ~ 1.0 from the size S of the circumference of intermediate location to the upstream extremity of first stage stator blades sheet nearest circumference between the described tail pipe and the tail pipe of other burners described of described burner and the ratio S/P of this size P.

In this gas turbine, relative to each downstream of the tail pipe that the inner surface of the pair of sidewalls of the tail pipe from any burner is connected respectively, arbitrary first stage stator blades sheet more closely exists in the circumferential, due to the existence of this first stage stator blades sheet, the pressure oscillation in the downstream of each tail pipe can be suppressed.

(7) in above-mentioned (1) to (6) in arbitrary gas turbine, with the spacing dimension P of multiple described first stage stator blades sheet for benchmark, be less than 0.2 from the size L of the described axis direction of downstream to the upstream extremity of described first stage stator blades sheet of described tail pipe and the ratio L/P of this size P.

In this gas turbine, relative to the downstream of tail pipe, first stage stator blades sheet more closely exists on the axis direction of tail pipe, therefore can suppress the pressure oscillation in the downstream of each tail pipe due to the existence of this first stage stator blades sheet.

Invention effect

In the present invention, the situation forming toll bar vortex row in the downstream of the downstream end face of tail pipe can be suppressed, the pressure oscillation of the downstream part of tail pipe can be suppressed.Therefore, according to the present invention, gas turbine proficiency can be improved.

Accompanying drawing explanation

Fig. 1 is the unitary side view major part of gas turbine cut open of one embodiment of the present invention.

Fig. 2 is the sectional view of the burner periphery of the gas turbine of one embodiment of the present invention.

Fig. 3 is the stereogram of the tail pipe of one embodiment of the present invention.

Fig. 4 is the sectional view in the downstream of the tail pipe of one embodiment of the present invention.

Fig. 5 is the coordinate diagram of the relation between the slope of the expression inclined plane of one embodiment of the present invention and pressure variance.

Fig. 6 is the key diagram of the expression tail pipe of one embodiment of the present invention and the position relationship of first stage stator blades sheet.

Fig. 7 is the key diagram of the pressure oscillation in the downstream of the expression tail pipe of one embodiment of the present invention, this figure (a) represents that circumferential ratio is the situation of 10%, this figure (b) represents that circumferential ratio is the situation of 22.5%, this figure (c) represents that circumferential ratio is the situation of 35%, and this figure (d) represents that circumferential ratio is the situation of 47.5%.

Fig. 8 is the coordinate diagram of the relation between the pressure variance in the downstream of the expression tail pipe of one embodiment of the present invention and circumferential ratio.

Fig. 9 is the sectional view in the downstream of the tail pipe of the variation of inclined plane for representing one embodiment of the present invention, and this figure (a) represents the first variation of inclined plane, and this figure (b) represents the second variation of inclined plane.

Figure 10 is the key diagram of the position relationship between the inclined plane of the expression tail pipe of the variation of one embodiment of the present invention and first stage stator blades sheet.

Detailed description of the invention

Below, be described in detail with reference to the embodiment of accompanying drawing to gas turbine of the present invention.

As shown in Figure 1, the gas turbine of present embodiment possesses: compress extraneous air and generate compressed-air actuated compressor 1; Fuel from fuel supply source is mixed with compressed air and makes this fuel combustion and generate multiple burners 10 of burning gases; Burning gases are utilized to carry out the turbine 2 driven.

Turbine 2 possesses shell 3 and the turbine rotor 5 rotated in this shell 3.Turbine rotor 5 have the stacked and rotor subject 6 that forms of multiple rotor disk and multiple rotor disk each in multiple moving vanes 7 from this rotor disk to radiation direction that extend from.That is, this turbine rotor 5 is multistage moving vane structure.

This turbine rotor 5 is such as connected with and carries out by the rotation of this turbine rotor 5 generator (not shown) that generates electricity.In addition, on shell 3, be fixed with from inner circumferential surface to the multiple stator blades 4 extended near the direction of rotor subject 6 at each upstream side of moving vane 7 at different levels.

Multiple burner 10 is centered by the rotation Ar of turbine rotor 5, be circumferentially equally spaced fixed on shell 3 each other.

As shown in Figure 2, burner 10 possesses the tail pipe 20 carried in the gas flow path 8 of turbine 2 from the gas access 9 of turbine 2 by the burning gases G of high temperature, high pressure and the fuel feeder 11 supplying fuel and compressed air Air in this tail pipe 20.The moving vane 7 of turbine 2 and stator blade 4 are configured in this gas flow path 8.Fuel feeder 11 possesses and is supplied in tail pipe 20 by pilot fuel X and in this tail pipe 20, form the pilot burner 12 of diffusion flame and main fuel Y and compressed air Air premixed are supplied in tail pipe 20 as pre-mixed gas and in this tail pipe 20, form multiple main burners 13 of premixed flame.

As shown in Figures 2 and 3, tail pipe 20, in tubular, has in inner circumferential side and supplies the main body 21 of burning gases G flowing and be located at the downstream end of main body 21 and the Outlet flange 31 of the Directional Extension towards the axis Ac away from tail pipe 20.

The cross sectional shape in the downstream of main body 21 is rectangle, and this main body 21 has the pair of sidewalls 22 opposite each other on circumferential C centered by the rotation Ar of turbine rotor 5 and the pair of sidewalls 23 opposite each other in radiation direction centered by this rotation Ar at its downstream portion.

As shown in Figure 4, the Outlet flange 31 arranged at the downstream end of main body 21 has from the downstream of main body 21 towards the flange body portion 32 of the Directional Extension of the axis Ac away from tail pipe 20 and the opposed portion 33 that extends from the outer rim in this flange body portion 32 towards upstream side.The downstream end face in this flange body portion 32 becomes the downstream end face 20ea of tail pipe 20.In addition, between the opposed portion 33 of the tail pipe 20 of this opposed portion 33 and burner 10 adjacent on circumferential C, the containment member 35 that the tail pipe of adjacent burner 10 is sealed each other is provided with.It should be noted that, in the present embodiment, the sidewall 22,23 of the part in the downstream of main body 21, the i.e. downstream portion of main body 21 and flange body portion 32 are formed by integrally formed product.

The inner surface 24 that pair of sidewalls 22 opposite each other on circumferential C is respective becomes inclined plane 25, this inclined plane 25 along with the downstream in the axis Ac direction towards tail pipe 20, and to tilting to the downstream 20e arriving tail pipe 20 gradually near the direction of the tail pipe 20 of other adjacent burners 10.That is, the downstream of inclined plane 25 is downstream 20e of tail pipe 20.

In tail pipe 20 towards the burning gases G of downstream flowing also flow to the direction of the inner surface 24 along sidewall 22 after flowing out tail pipe 20 in, the downstream of the downstream end face 20ea therefore sometimes in flange body portion 32 formation toll bar vortex arranges.

In the present embodiment, the inner surface 24 of the sidewall 22 of the downstream portion of tail pipe 20 becomes inclined plane 25, and therefore not form the situation of inclined plane 25 little for the downstream end face 20ea in flange body portion 32 and the inner surface 24 angulation specific inner surface 24 of sidewall 22.Therefore, in the present embodiment, the downstream of the downstream end face 20ea in flange body portion 32 can be suppressed to form the situation of toll bar vortex row, the pressure oscillation of the downstream part of tail pipe 20 can be suppressed.

At this, the pressure variance for the downstream part of the tail pipe 20 when changing the slope of this inclined plane 25 is simulated, and is therefore described this analog result.It should be noted that, in this simulation, as shown in Figure 4, with the size B of the circumferential C of (downstream of=tail pipe 20) from upstream extremity 25s to downstream 20e of inclined plane 25 for benchmark, the size A in axis Ac direction from upstream extremity 25s to downstream 20e and the ratio A/B of this size B is defined as the slope of inclined plane 25.

Known as shown in Figure 5, as the result of this simulation, slope A/B be more than 1 and less than 8 time, the pressure variance Δ P of the downstream part of burner 10 diminishes.This is because, when slope A/B is less than 1 and when being greater than 8, tilts too urgent or excessively slow, fully cannot obtain the effect as inclined plane 25.In addition, also the known slope A/B when inclined plane 25 be more than 2 and less than 6 time, pressure variance Δ P extremely diminishes.It should be noted that, along with in tail pipe 20, the flow velocity of the burning gases G of flowing increases, pressure variance Δ P also increases, even if but in tail pipe 20 flow velocity of burning gases G of flowing change, the slope A/B of inclined plane 25 is also substantially identical with the relation between pressure variance Δ P.

Therefore, the preferable range Ra of the slope A/B of inclined plane 25 is more than 1 and less than 8, and more preferably scope Rb is more than 2 and less than 6.

In addition, at this, the pressure variance of the downstream side portion office of the burner 10 when changing the relative position of tail pipe 20 and first stage stator blades sheet 4a is simulated, therefore this analog result is also described.Specifically, as shown in Figure 6, for with the spacing dimension P of the circumferential C of multiple first stage stator blades sheet 4a for benchmark, from the tail pipe 20 of the burner 10a determined and and the tail pipe 20 of its other burners 10b adjoined in the side of circumferential C between intermediate location M to the upstream extremity 4s at the nearest first stage stator blades sheet 4a in the side of circumferential C the size S of circumferential C and the ratio S/P (hereinafter referred to as circumferential ratio S/P) of this size P and pressure variance Δ P relation simulate.

It should be noted that, this simulation is 2:3 by the quantity Nc of burner 10 with the ratio of the quantity Ns of first stage stator blades sheet 4a and the slope A/B of the inclined plane 25 of tail pipe 20 2.75 carries out.In addition, this simulation is undertaken by being set to 12% with the ratio L/P (hereinafter referred to as axis direction ratio L/P) of the size L the axis Ac direction of spacing dimension P for benchmark and from the downstream 20e to the upstream extremity 4s of first stage stator blades sheet 4a of tail pipe 20 and this size P.

As shown in Figure 8, when axis direction ratio L/P is 12%, circumferential ratio S/P is 0% ~ 5%, there is astable pressure oscillation hardly.But when circumferential ratio S/P is more than 5%, start to find larger pressure variance Δ P, when circumferential ratio S/P becomes 10%, pressure variance Δ P increases further.

As shown in Fig. 7 (a), when circumferential ratio S/P is 10%, the burner 10a determined tail pipe 20 and and the tail pipe 20 of its other burners 10b adjoined in the side of circumferential C between downstream, do not find astable pressure oscillation, but the burner 10a determined tail pipe 20 and and the tail pipe 20 of its other burners 10c adjoined at the opposite side of circumferential C between downstream, produce toll bar vortex row V, create larger astable pressure oscillation.This consider be because, from the tail pipe 20 of the burner 10a determined and and the tail pipe 20 of its other burners 10c adjoined at the opposite side of circumferential C between the cause that increases of the size of circumferential C to the upstream extremity 4s of first stage stator blades sheet 4a nearest circumferential C.It should be noted that, the fine rule in Fig. 7 represents isostatic pressed line.

Therefore, when circumferential ratio S/P becomes 10%, can think that pressure variance Δ P increases.Wherein, in this simulation, because the slope A/B of inclined plane 25 is more preferably 2.75 in scope Rb (more than 2 and less than 6), therefore compared with situation not forming inclined plane 25 etc., P is less for pressure variance Δ.

Pressure variance Δ P, when circumferential ratio S/P is 20%, sharply diminishes as shown in Figure 8, when circumferential ratio S/P is 22.5%, does not almost find astable pressure oscillation.As shown in Fig. 7 (b), when circumferential ratio S/P is 22.5%, the burner 10a determined tail pipe 20 and and the tail pipe 20 of its other burners 10b adjoined in the side of circumferential C between downstream and the tail pipe 20 of burner 10a determined and and the tail pipe 20 of its other burners 10c adjoined at the opposite side of circumferential C between downstream, almost do not find astable pressure oscillation yet.

As shown in Fig. 7 (c) and Fig. 7 (d), when circumferential ratio S/P is 35%, 47.5%, almost do not find astable pressure oscillation yet.But as shown in Figure 8, when circumferential ratio S/P is more than 55%, again start to find larger pressure variance Δ P, when circumferential ratio S/P becomes 60%, pressure variance Δ P increases further.This is because, from the tail pipe 20 of the burner 10a determined and and the tail pipe 20 of its other burners 10b adjoined in the side of circumferential C between the cause that increases of the size of circumferential C to the upstream extremity 4s of first stage stator blades sheet 4a nearest circumferential C.That is, can think when circumferential ratio S/P is 60%, when being 10% with circumferential ratio S/P, produce identical phenomenon with substantially identical reason.

This pressure variance Δ P, when circumferential ratio S/P becomes 70%, sharply diminishes, and when circumferential ratio S/P becomes 72.5%, does not almost find astable pressure oscillation.Below, until circumferential ratio S/P becomes 100%, almost astable pressure oscillation is not found.

Known as previously discussed, when circumferential ratio S/P is 0% ~ 5%, 20% ~ 55%, 70% ~ 100%, almost do not find astable pressure oscillation, the pressure variance Δ P of the downstream part of tail pipe 20 extremely diminishes.That is, known, for circumferential ratio S/P, preferable range Rc is 0% ~ 5%, 20% ~ 55%, 70% ~ 100%.

In addition, at this, change axis direction ratio L/P, as described above, the relation of circumferential ratio S/P and pressure variance Δ P is simulated.

As shown in Figure 8, when axis direction ratio L/P is 18%, 20% time, 27% time, the tendency that the change of pressure variance Δ P is identical when to have with described axis direction ratio L/P be 12% relative to the change of circumferential ratio S/P.Namely, in the same manner as when described axis direction ratio L/P is 12%, when circumferential ratio S/P is 0% ~ 5%, 20% ~ 55%, 70% ~ 100%, compared with the situation being 5% ~ 20%, 55% ~ 70% with circumferential ratio S/P, the pressure variance Δ P of the downstream part of burner 10 diminishes relatively.

But, it is known when axis direction ratio L/P is 18% and 20%, when circumferential ratio S/P is 0% ~ 5%, 20% ~ 55%, 70% ~ 100%, in the same manner as when described axis direction ratio L/P is 12%, almost do not find astable pressure oscillation, the absolute value of pressure variance Δ P is less, but when axis direction ratio L/P is 27%, even if when circumferential ratio S/P is 0% ~ 5%, 20% ~ 55%, 70% ~ 100%, the absolute value of pressure variance Δ P also increases.

That is, known by axis direction ratio L/P is set to less than 20%, pressure variance Δ P diminishes.

In addition, above analog result is the quantity Nc of burner 10 is the situation of 2:3 with the ratio of the quantity Ns of first stage stator blades sheet 4a, even if but when Nc:Ns=2:5, Nc:Ns=2:7, more than Nc:Ns=2:9, relation between the pressure variance Δ P of the relative position between tail pipe 20 and first stage stator blades sheet 4a and the downstream side portion office of tail pipe 20, also can think and can obtain result similar to the above.Wherein, the quantity Ns of first stage stator blades sheet 4a more increases relative to the quantity Nc of burner 10, no matter circumferential ratio S/P, axis direction ratio L/P are any value, the absolute value of pressure variance Δ P when pressure variance Δ P increases also more reduces, if the quantity Ns of first stage stator blades sheet 4a increases further, then no matter circumferential ratio S/P, axis direction ratio L/P are any value, also almost do not find astable pressure oscillation.

It should be noted that, be 1: during natural number at the quantity Nc of burner 10 with the ratio of the quantity Ns of first stage stator blades sheet 4a, can between the tail pipe 20 of each burner 10 and other tail pipes 20 be adjacent immediately below configure the upstream extremity 4s of first stage stator blades sheet 4a, therefore by so configuring first stage stator blades sheet 4a, astable pressure oscillation can almost be eliminated.

Next, the various variation of the inclined plane 25 of tail pipe 20 are described.

The entirety of the end of the trip from it 25s to downstream 20e of the inclined plane 25 of above embodiment is plane, but this inclined plane 25 does not need entirety for plane, can comprise curved surface at least partially.

Specifically as shown in Figure 9, this curved surface is near the axis Ac of tail pipe 20 and curved surface 26a, 26b, 26c of bloating smoothly towards the side in downstream.Such as, as shown in Fig. 9 (a), the juncture area of the downstream end face 20ea in curved surface 26a and inclined plane 25 and flange body portion 32 is consistent, namely the downstream of this curved surface 26a and the downstream 20e of inclined plane 25 consistent.In addition, for curved surface 26b, the upstream extremity of this curved surface 26b is consistent with the upstream extremity 25s of inclined plane 25.In addition, as shown in Fig. 9 (b), inclined plane 25 entirety is curved surface 26c.

Like this, when the curved surface of employing at least partially of inclined plane 25, there is not the flowing of burning gases G towards the position changed sharp, therefore, it is possible to suppress the situation forming toll bar vortex row in the downstream of the downstream end face 20ea of tail pipe 20 further, the pressure oscillation of the downstream part of tail pipe 20 more effectively can be suppressed.Therefore, when inclined plane 25 adopt curved surface at least partially, the preferable range Ra of the slope A/B of inclined plane 25 is less than 8 wider than described above more than 1.

In addition, in the above embodiment, the inner surface 24 that pair of sidewalls 22 opposite each other on circumferential C is respective becomes inclined plane 25, even if but only the inner surface 24 of either party become inclined plane 25, also can suppress the pressure oscillation of the downstream part of tail pipe 20.In this case, as shown in Figure 10, on circumferential C, relative to first stage stator blades sheet 4a upstream extremity 4s and the side that the downstream 4e of first stage stator blades sheet 4a exists is set to blade lean side Ca when, the inner surface 24 of the sidewall 22 (being 22b in case of fig. 10) of the blade lean side Ca in pair of sidewalls opposite each other on circumferential C 22 (being 22a and 22b in case of fig. 10) preferably becomes inclined plane 25.This is because, the flowing of the burning gases G guided by inclined plane 25 towards with by the direction of the upstream extremity 4s of first stage stator blades sheet 4a and the line segment that downstream 4e links, i.e. chord of blade, the flowing of burning gases G that in other words guided by first stage stator blades sheet 4a towards almost identical, become smooth and easy from tail pipe 20 towards the flowing of the burning gases G of first stage stator blades sheet 4a, effectively can suppress the pressure oscillation of the downstream part of tail pipe 20.

It should be noted that, as mentioned above, even if the inner surface 24 of the only sidewall 22 (being 22a or 22b in case of fig. 10) of either party in pair of sidewalls 22 opposite each other on circumferential C becomes inclined plane 25, the relation between the relative position of tail pipe 20 and first stage stator blades sheet 4a and the pressure variance Δ P of the downstream side portion office of tail pipe 20 is also substantially identical with above analog result.

Symbol description:

1: compressor, 2: turbine, 3: shell, 4: stator blade, 4a: first stage stator blades sheet, 4s:(stator blade) upstream extremity, 4e:(stator blade) downstream, 5: turbine rotor, 6: rotor subject, 7: moving vane, 8: gas flow path, 9: gas access, 10: burner, 20: tail pipe, 20e:(tail pipe or inclined plane) downstream, 20ea:(tail pipe or flange body portion) downstream end face, 21: main body, 22, 22a, 22b, 23: sidewall, 24: inner surface, 25: inclined plane, 25s:(inclined plane) upstream extremity, 26a, 26b, 26c: curved surface.

Claims

1. a gas turbine, it possesses: mixed with compressed air by fuel and make this fuel combustion and generate multiple burners of burning gases; There is the turbine utilizing the burning gases from multiple described burner to carry out the rotor rotated,

Multiple described burner configures in the form of a ring centered by described rotor, and has the tail pipe of the gas access conveying burning gases to described turbine, in described gas turbine,

At the downstream portion of the described tail pipe of described burner, the inner surface of the sidewall of at least one party in pair of sidewalls opposite each other in the circumference of described rotor becomes inclined plane, this inclined plane is along with the downstream of the axis direction towards described tail pipe, and to gradually near the direction of the tail pipe of other adjacent burners, tilt to the downstream arriving described tail pipe

With described inclined plane from upstream extremity to downstream till the size B of circumference for benchmark, described inclined plane be more than 1 and less than 8 from the size A of axis direction of described upstream extremity to described downstream and the ratio A/B of this size B.

2. gas turbine according to claim 1, wherein,

Described turbine has the multiple first stage stator blades sheets configured in the form of a ring and along described gas access centered by described rotor, the chord of blade direction that the chord of blade of described first stage stator blades sheet extends relative to described peripheral, oblique,

In the circumferential direction, when the side that the downstream of this first stage stator blades sheet exists being set to blade lean side at the upstream extremity relative to described first stage stator blades sheet, the sidewall of the described at least one party of described tail pipe is the sidewall of the blade lean side in sidewall described in a pair opposite each other in the circumferential in described tail pipe.

3. gas turbine according to claim 1, wherein,

Described in a pair opposite each other in the circumferential in described tail pipe, the described inner surface of sidewall both sides becomes described inclined plane.

4. a gas turbine, it possesses: mixed with compressed air by fuel and make this fuel combustion and generate multiple burners of burning gases; There is the turbine utilizing the burning gases from multiple described burner to carry out the rotor rotated,

Described inclined plane comprises curved surface at least partially, and this curved surface is bloating near the axis of described tail pipe and the side towards downstream.

5. a gas turbine, it possesses: mixed with compressed air by fuel and make this fuel combustion and generate multiple burners of burning gases; There is the turbine utilizing the burning gases from multiple described burner to carry out the rotor rotated,

Described turbine has the multiple first stage stator blades sheets configured in the form of a ring and along described gas access centered by described rotor,

The quantity of described burner is the odd number of more than 2: 3 with the ratio of the quantity of described first stage stator blades sheet,

With the spacing dimension P of multiple described first stage stator blades sheet for benchmark, be less than 0.05,0.2 ~ 0.55 or between 0.7 ~ 1.0 from the size S of the circumference of intermediate location to the upstream extremity of first stage stator blades sheet nearest circumference between the described tail pipe and the tail pipe of other burners described of described burner and the ratio S/P of this size P.

6. the gas turbine according to claim 2 or 5, wherein,

With the spacing dimension P of multiple described first stage stator blades sheet for benchmark, be less than 0.2 from the size L of the described axis direction of downstream to the upstream extremity of described first stage stator blades sheet of described tail pipe and the ratio L/P of this size P.

7. a burner, circumferentially arranges multiple adjacent to one another centered by the rotation of the rotor of turbine, and generates the burning gases for making described rotor rotate, wherein,

Described burner is for tail pipe, and this tail pipe has pair of sidewalls opposite each other in the circumference centered by described rotation, and carries burning gases to the gas access of described turbine,

The inner surface of the sidewall of at least one party in the pair of sidewalls opposite each other in the circumferential direction of described tail pipe becomes inclined plane, this inclined plane is along with the downstream of the axis direction towards described tail pipe, and to gradually near the direction of the tail pipe of other adjacent burners, tilt to the downstream arriving described tail pipe