CN205079262U - Annular wall of turbine engine combustion chamber, including its combustion chamber and turbine engine - Google Patents
Annular wall of turbine engine combustion chamber, including its combustion chamber and turbine engine Download PDFInfo
- Publication number
- CN205079262U CN205079262U CN201520187088.2U CN201520187088U CN205079262U CN 205079262 U CN205079262 U CN 205079262U CN 201520187088 U CN201520187088 U CN 201520187088U CN 205079262 U CN205079262 U CN 205079262U
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- Prior art keywords
- annular wall
- cooling holes
- combustion chamber
- cooling
- axial
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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
- F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
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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
- 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
- F23R2900/03041—Effusion cooled combustion chamber walls or domes
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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
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The utility model discloses an annular wall of turbine engine combustion chamber, this wall include cold side (16a, 18a) and heat side (16b, 18b), the at least a plurality of gyration cooling holes of distribution on axially a plurality of circumference of spaced are arranged each other, in the gyration cooling hole geometric axis in every hole arrange perpendicular to combustion gas's axial flow orientation D and for in the plane of the normal line N slope of annular wall, it still includes the follow multirow gyration cooling hole low reaches and next -door neighbour are used for being connected to the upper reaches of the flange of combustion chamber circular casing, one row at least axial cooling hole (36), for the slope axis that has them on the normal line N's of annular wall the axial direction D, every cooling kong zaire side provides opening on axial direction D part (42) in the axial cooling hole, in order to cause cooling air's membrane more is close to the tangent line of hot wall is discharged. The utility model also discloses a combustion chamber and turbine engine.
Description
Technical field
The utility model relates to the usual field of turbine engine combustion chamber.It relates more particularly to following current or the annular wall of reverse-flow combustion chamber of the method cooling by being called " multiple punching ".
Background technology
Normally, the combustion chamber of annular turbine engine is made up of inner annular wall (or interior guard shield) and annular wall (or outer shield), this wall, and to be linked together in upstream by the transverse wall of formation combustion chamber end wall by flange (or by not having perforated breasting face) respectively in the housing that downstream is connected to combustion chamber and shell.
Multiple hole and various hole is provided, for the inner side allowing the air of combustion chamber ambient dynamic to penetrate into combustion chamber with outer shield in each.
Therefore, the hole being called " master " hole and these guard shields that pierced being called " blending " hole are formed, to deliver air to the inner side of combustion chamber.Air through main hole is conducive to producing the air/fuel mixture burnt in a combustion chamber, and the air coming from blending hole is for dilution air/fuel mixture.
Due to the gas that the burning of air/fuel mixture produces, interior and outer shield is subject to high temperature action.
In order to cool them, be called that the additional holes in the hole of " multiple punching " is worn these guard shields and formed on their whole area.The hole allowing the air of combustion chamber flows outside to penetrate into these multiple punching inside combustion chamber forms the film of cooling-air thus along guard shield, and they have usually from the axial type of upstream, blending hole and the revolution type that has from its downstream.
Unfortunately, the hole of the revolution multiple punching in blending hole downstream causes the pivotal sizable restriction of combustor exit place residual level, therefore be unfavorable for the efficiency of the high pressure nozzle (HPN) worked thus thereon, thus reduce total consumption of engine.That why known for be located close in flange upstream and outer shield each in last a few round, turn back to and have axial multiple punching, this flange is for connecting the shell of combustion chamber.Which results in the cooling defect be harmful to very much in this most important region, and implied (under creep and tired synergy) high-caliber risk that crackle will be formed very soon, need thus to avoid or reduce this risk at least considerably.
Utility model content
The purpose of this utility model is by using annular firing locular wall, and the cooling optimizing revolution multiple punching downstream alleviates these defects, and this annular firing locular wall provides enough coolings in the region being located close to flange upstream, and this flange is connected to burning chamber shell.
For this reason, the utility model provides the annular wall for turbine engine combustion chamber, this wall comprises cold side and hot side, annular wall comprises at least multiple revolution Cooling Holes on the multiple circumference rows being distributed in each other axially interval, in described revolution Cooling Holes, the geometrical axis in each hole is arranged in the plane that the axial flow direction D perpendicular to burning gases and the normal N relative to described annular wall tilt, the feature of annular wall is that it also comprises, from described many line pivotings Cooling Holes downstream and the upstream being close to the flange for being connected to described combustion chamber circular casing, the axial Cooling Holes of at least one row, there is their tilt axis in the described axial direction D of the normal N relative to described annular wall, in described axial Cooling Holes, each Cooling Holes provides the flared section on described axial direction D in hot side, discharge closer to the tangent line of described hot wall to cause the film of described cooling-air.
By advancing to the hole having and outwards open hole from the cylindrical bore of routine, improve the adiabatic efficiency of the multiple punching film in Cooling Holes downstream, and guided this cooling-air layer that row downstream produces better, and provide more efficient Thermal protection.
Advantageously, flared section has scope the inclined angle alpha of 15 ° to 40 ° relative to the axis of described axial Cooling Holes.
In favourable embodiment, the direction relative to described axial direction D transverse direction also provides the described flared section of described axial Cooling Holes, to increase the lateral overlap of described cooling-air film.Then described flared section preferably has relative to described axial direction D scope at 7.5 ° to 20 ° maximum aperture angle β.
Advantageously, provide the axial Cooling Holes of two rows that spacing distance is not less than 1.5 millimeters (mm), and described flared section is spaced the distance being not less than 0.5mm on the direction perpendicular to described axial direction D.
Preferably, also comprise the additional Cooling Holes of at least two rows in the transitional region of wall between described multiple revolution Cooling Holes and the axial Cooling Holes of described at least one row, the axis of this additional Cooling Holes tilts and determines inclination angle relative to the described plane perpendicular to described axial direction D.
In the embodiment of an expection, wall can comprise the Cooling Holes of two additional rows, first row has the inclination angle of 30 °, second row has the inclination angle of 60 °, or the Cooling Holes of in fact multiple additional row, have inclinations angle different respectively, this inclination angle distributes regularly in 0 ° to 90 ° scope.
By making flowing smooth and easy, the transitional region of this revolution-axial multiple punching is for reducing the thermograde starting starting point place at crackle.Because more effective mixing obtained thus, improve the mean temperature profile at combustor exit place.
The utility model also provides combustion chamber and turbogenerator, and turbogenerator has the combustion chamber comprising above-mentioned annular wall.
Accompanying drawing explanation
Can manifest other features and advantages of the present invention from reference to the following describes of carrying out of accompanying drawing, accompanying drawing represents the embodiment not having limited features.In the accompanying drawings:
Fig. 1 is the longitudinal sectional drawing of turbine engine combustion chamber in its environment.
Fig. 2 is the part expanded view of one of the annular wall of Fig. 1 combustion chamber in embodiment of the present invention.
Fig. 3 is the fragmentary cross-sectional view of Fig. 2 annular wall around blending hole.
Fig. 4 is the side view of the Cooling Holes of the present invention being arranged in the direct upstream of flange.
Fig. 5 A, 5B and 5C are the planes of three change modes of Fig. 4 Cooling Holes.With
Fig. 6 is the partial plan representing longitudinal direction and the space, azimuth existed between two holes of arranging continuously.
Detailed description of the invention
Fig. 1 represents that turbine engine combustion chamber 10 is in its environment.This turbogenerator comprises part (not shown) of calming the anger especially, and wherein air was compressed before being injected into burning chamber shell 12, is then ejected in the combustion chamber 10 be arranged on wherein.The air of compression to be introduced in combustion chamber and burned wherein before and fuel mix.Then the hot gas coming from burning is directed to the pressure turbine 14 arranged at combustor exit place.
Combustion chamber has annular type.It comprises inner annular wall 16 and annular wall 18, and both are connected to burning chamber shell by flange and united by the transverse wall 20 forming combustion chamber end wall in upstream.Combustion chamber can be as directed downstream combustion room, or it can be reverse-flow combustion chamber.In this case, return bend is placed between combustion chamber and turbomachine injection nozzle.
In and annular wall 16 and 18 along the longitudinal axis 22 relative to turbogenerator tilt any longitudinal axis extend.Combustion chamber end wall 20 provides multiple opening 20A, has the fuel injector 21 be arranged on wherein in this opening 20A.
Burning chamber shell 12, is made up of inner casing 12a and shell 12b, and it coordinates to limit annular space 26 with combustion chamber 10, and this annular space 26 receives for burning, for blending and the compressed air for cooling combustion room.
In and annular wall 16 and 18 there is respective cold side 16a, the 18a of the annular space 26 in the face of the flowing of wherein compressed air, and towards each self-heating side 16b, the 18b inside combustion chamber.
Combustion chamber 10 is divided into " master " region (or combustion zone) and is positioned at " secondary " region (or blending region) in main region downstream (wherein, " downstream " is construed as relative with the total axial direction coming from the air-flow that inside combustion chamber, air/fuel mixture burns and represents with arrow D).
The air carried to the main region of combustion chamber is introduced by the main hole 28 of circumference row, through in combustion chamber and annular wall 16 and 18 form this main hole 28 around the whole circumference of these annular wall.The air carried to the secondary region of combustion chamber is introduced by multiple blending hole 30, and the whole circumference formation of interior and annular wall 16 and 18 around these annular wall of combustion chamber is also passed in this blending hole 30.Blending hole 30 also circumferentially arranges alignment, and this circumference row offsets to those row's downstream axial from main hole 28, and they can have different diameters, the large hole replaced especially and duck eye, as shown in Figure 2.
In order to cool be subject to burning gases high temperature action combustion chamber in and annular wall 16 and 18, provide multiple Cooling Holes 32,34,36 and 28 (shown in Fig. 2 to Fig. 5), for by multiple punching cooling wall 16,18.For reverse-flow combustion chamber (not shown), return bend also has this multiple punching usually.
This some holes of First Series arranges distribution with multiple circumference, and the plurality of circumference arranges each other the outlet of whole surface as far as blending hole 30 of the annular wall of axially interval and covering combustion chamber.
The quantity of these Cooling Holes 32 is identical in that, in each row with diameter d 1.In given row, the pitch P 1 of two bore dias is constant, and can be identical or different between row.And, arrange the Cooling Holes of adjacent row so that hole 32 is decussate structure, as shown in Figure 2.
As shown in Figure 3, Cooling Holes 32 has the tiltangleθ 1 of the normal N relative to annular wall 16,18 usually, and they are formed through this annular wall.This tiltangleθ 1 can make the air that passes via this some holes form air film along hot side 16b, 18b of annular wall.With aclinal boring ratio comparatively, they are for increasing the area of cooled annular wall.In addition, the tiltangleθ 1 of Cooling Holes 32 be directed to so that formed in this way air film burning gases inside combustion chamber flow direction on flowing (representing with arrow D in fig. 2).
But, in context of the present utility model, the Cooling Holes (Reference numeral 34 provided) of the second series in blending hole 30 downstream is similarly distributed on multiple circumference row, in order to carry the air film flowed on the direction of the axial direction D perpendicular to combustion gas flow.This multiple punching, in the description hereinafter referred to as " revolution " multiple punching, contrary with " axis " multiple punching of blending hole upstream Cooling Holes, by making rotary hole closer to blending hole, the cooling of annular wall can be improved.
In any given row porose 34 all there is identical diameter d 2, this diameter d 2 can be identical or different with the diameter d 1 of Cooling Holes 32, the pitch P 2 of their alternate constant, this pitch P 2 can and Cooling Holes 32 between pitch P 1 identical or different, and they have tiltangleθ 2, this tiltangleθ 2 can be identical or different with the tiltangleθ 1 of Cooling Holes 32, but be arranged in vertical plane.
Illustrate, for be made up of metal or ceramic material and there is the annular wall 16,18 of 0.6mm to 3.5mm ranges of thicknesses, the diameter d 1 of Cooling Holes or d2 can be positioned at the scope of 0.3mm to 1mm, pitch P 1 or p2 can be positioned at the scope of 1mm to 10mm, and tiltangleθ 1 or θ 2 can be positioned at the scope of+30 ° to+70 °, and can be+60 ° especially.By comparing, for the annular wall with same characteristic features, main hole 28 and blending hole 30 have the diameter of 4mm to the 20mm order of magnitude.
The cooling requirement according to expecting should be observed, also different tiltangleθ, diameter d and pitch P can be provided in given area, the cooling in highest level thermal stress part is being subject to densification, such as, be close to the cooling in large blending hole downstream part, when blending hole is formed as large and aperture alternately, as shown in Figure 2.
In order to avoid the efficiency of impact to voltage nozzle, must pass through combustor exit place in the 3rd series of apertures (given Reference numeral 36) and introduce axial multiple punching, turn round level to reduce local, and more particularly so do (Fig. 2) from the First Transition axis 38A being positioned at high pressure nozzle upstream.Also preferably recommend to provide with revolution-to the multiple punching in-axial transitions region, this transitional region to terminate and from the second transition axis 38B being located thereon trip at this First Transition axis, to make flowing smooth and easy, and thus reduce cause crackle to start thermograde.Because more effective mixing obtained thus, improve combustor exit place mean temperature profile.Illustrate, and as shown, this transitional region can manufacture on the additional Cooling Holes 40 of two rows, often arrangement is set to, such as, in each plane tilted relative to axial direction D, one is 30 °, another is 60 °, and in these clinoplains other parameter of this some holes, namely, diameter d 2, pitch P 2 and tiltangleθ 2 remain unchanged (this embodiment is not restrictive, and transitional region can have three rows, and the inclination angle of its mesopore is 22.5 °, 45 ° and 67.5 ° respectively).
In the utility model, the cooling fluid (air) of this axial multiple punching that suggestion utilizes revolution multiple punching outlet place to arrange better, by from the Part I of wall columniform get into the cave through, to be manufactured on the hole that the Part II of wall extends, so that open in their exits on axial direction D, therefore improve the adiabatic efficiency of the multiple punching film in Cooling Holes downstream.In other words, the cooling-air layer produced from row downstream is guided better and is provided more effective Thermal protection.The seen thermal force of these parts (or the region in space) is greatly reduced, to improve their thermo-mechanical property and relevant useful life (for immovable mechanical stress).
For this reason, and as shown in Figure 4, the Cooling Holes 36 of next-door neighbour flange upstream has the distance x (x<0) of the length L being less than hole (normally, x is positioned at the scope of 1/3 to 2/3L), Part I, it is calibrated and for calibrating cooling and having the residue length (L-x) in hole, and end at the hot side 16b of annular wall in flared section 42, the Part II at 18b place, it is made to have Frusto-conical shape substantially, with the inclined angle alpha relative to axially bored line, its scope is at 15 ° to 40 °, with " pressure " air stream against hot wall.
As what can see in the plane of Fig. 5 A, this flared section 42 can only be formed on axial direction D, or as shown in figures 5 b and 5 c, it also can be formed in transverse plane, then this frusto-conically shaped portion advantageously has the angular aperture β relative to axial direction D, and its scope is at 7.5 ° to 20 °.
More particularly, when axial multiple punching region has at least two row's Cooling Holes 36, as shown in Figure 6, advantageously this some holes is by longitudinally and in azimuth (on axial direction D) interval minimum range separately (writing Δ and Γ), such Δ >0.5mm and Γ >1.5mm.
This structure opening outlet, be only the efficiency comparison that cylindrical hole obtains with use prior art, Cooling Holes 36 is for obtaining more effective film.The increase of this efficiency is the film owing to carrying along the injection direction closer to hot wall tangent line, because lateral overlap and the minimizing due to the momentum ratio (that is, the momentum ratio between hot side and cold side) of given following speed better cause.Thus, decrease the speed that outlet is sprayed, and promote that film is to the tack of hot wall, leaves the risk in boundary layer because which limit film.
Thus, the utility model can be observed for low blowing speed (as application usually in flange upstream region), finds according to efficiency of spraying from single row of holes of the present invention even not bad than the efficiency in two row common cylindrical shaped holes.
The estimation of improvement of the present utility model has been obtained by the temperature of the combustion chamber, axial multiple punching place calculating combustion chamber inner casing.Observe the temperature for this material, the decline of about 10 DEG C to 50 DEG C.Time span to creep resisting estimation improves (that is, the useful life aspect in described region) can be as the same in a factor in two factors (especially according to the metal material of relevant mechanical stress levels with hypothesis nickel-base alloy type).
Therefore, use the utility model, cooling is optimized by more efficient multiple punching, by reducing the quantity (effect by the increase azimuth pitch caused by the hole owing to opening) in hole and passing through to reduce thermal stress, reduce mechanical stress, improve the useful life of combustion chamber and flange.
Claims (10)
1. for the annular wall (16 of turbine engine combustion chamber (10), 18), this wall comprises cold side (16a, 18a) with hot side (16b, 18b), annular wall comprise be distributed in each other axially interval multiple circumferential row on multiple revolution Cooling Holes (34), in described revolution Cooling Holes, the geometrical axis in each hole is arranged in the plane that the axial flow direction D perpendicular to burning gases and the normal N relative to described annular wall tilt, the feature of annular wall is: it also comprises from described many line pivotings Cooling Holes downstream and is close to for being connected to described combustion chamber circular casing (12a, the upstream of flange 12b), the axial Cooling Holes of at least one row (36), the described axial direction D of the normal N relative to described annular wall has their tilt axis, in described axial Cooling Holes, each Cooling Holes provides the flared section on described axial direction D (42) in hot side, discharge closer to the tangent line of described hot side to cause the film of described cooling-air.
2. annular wall according to claim 1, is characterized in that: flared section has scope the inclined angle alpha of 15 ° to 40 ° relative to the axis of described axial Cooling Holes.
3. annular wall according to claim 1, is characterized in that: the described flared section also providing described axial Cooling Holes on the direction relative to described axial direction D transverse direction, to increase the lateral overlap of described cooling-air film.
4. annular wall according to claim 3, is characterized in that: described flared section has relative to the maximum aperture angle β of described axial direction D scope at 7.5 ° to 20 °.
5. annular wall according to claim 1, is characterized in that: it comprises the axial Cooling Holes of two rows that spacing distance is not less than 1.5 millimeters, and described flared section is spaced the distance being not less than 0.5mm on the direction perpendicular to described axial direction D.
6. annular wall according to claim 1, it is characterized in that: it is also included in the additional Cooling Holes (40) of at least two rows in the transitional region (38A, 38B) between described multiple revolution Cooling Holes and the axial Cooling Holes of described at least one row, and the axis of this additional Cooling Holes tilts and determines inclination angle relative to the described plane perpendicular to described axial direction D.
7. annular wall according to claim 6, is characterized in that: it comprises the Cooling Holes of two additional rows, and first row has the inclination angle of 30 °, and second row has the inclination angle of 60 °.
8. annular wall according to claim 6, is characterized in that: it comprises the Cooling Holes of multiple additional row, and have inclinations angle different respectively, this inclination angle distributes regularly in 0 ° to 90 ° scope.
9. a turbine engine combustion chamber (10), it comprises at least one annular wall according to claim 1 (16,18).
10. a turbogenerator, it comprises combustion chamber (10), and this combustion chamber comprises at least one annular wall according to claim 1 (16,18).
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR1452800 | 2014-03-31 | ||
| FR1452800A FR3019270B1 (en) | 2014-03-31 | 2014-03-31 | ANNULAR ROOM OF COMBUSTION CHAMBER HAVING IMPROVED COOLING BODIES AT FLANGE JOINT LEVELS |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205079262U true CN205079262U (en) | 2016-03-09 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520187088.2U Active CN205079262U (en) | 2014-03-31 | 2015-03-31 | Annular wall of turbine engine combustion chamber, including its combustion chamber and turbine engine |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN205079262U (en) |
| FR (1) | FR3019270B1 (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109668173A (en) * | 2019-01-14 | 2019-04-23 | 西安增材制造国家研究院有限公司 | A kind of evaporation tubular type compact combustion chamber |
| CN115218214A (en) * | 2021-04-19 | 2022-10-21 | 通用电气公司 | Dilution hole of burner |
| CN115342388A (en) * | 2021-05-14 | 2022-11-15 | 通用电气公司 | Combustor dilution with vortex generating turbulators |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7812282B2 (en) * | 2007-03-15 | 2010-10-12 | Honeywell International Inc. | Methods of forming fan-shaped effusion holes in combustors |
| FR2982008B1 (en) * | 2011-10-26 | 2013-12-13 | Snecma | ANNULAR ROOM OF COMBUSTION CHAMBER WITH IMPROVED COOLING AT THE PRIMARY HOLES AND DILUTION HOLES |
-
2014
- 2014-03-31 FR FR1452800A patent/FR3019270B1/en active Active
-
2015
- 2015-03-31 CN CN201520187088.2U patent/CN205079262U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109668173A (en) * | 2019-01-14 | 2019-04-23 | 西安增材制造国家研究院有限公司 | A kind of evaporation tubular type compact combustion chamber |
| CN109668173B (en) * | 2019-01-14 | 2019-11-26 | 西安增材制造国家研究院有限公司 | A kind of evaporation tubular type compact combustion chamber |
| CN115218214A (en) * | 2021-04-19 | 2022-10-21 | 通用电气公司 | Dilution hole of burner |
| CN115342388A (en) * | 2021-05-14 | 2022-11-15 | 通用电气公司 | Combustor dilution with vortex generating turbulators |
Also Published As
| Publication number | Publication date |
|---|---|
| FR3019270A1 (en) | 2015-10-02 |
| FR3019270B1 (en) | 2016-04-15 |
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