WO2012153040A1 - Dispositif pour le montage d'une bougie d'allumage dans une chambre de combustion de moteur a turbine a gaz - Google Patents
Dispositif pour le montage d'une bougie d'allumage dans une chambre de combustion de moteur a turbine a gaz Download PDFInfo
- Publication number
- WO2012153040A1 WO2012153040A1 PCT/FR2012/050984 FR2012050984W WO2012153040A1 WO 2012153040 A1 WO2012153040 A1 WO 2012153040A1 FR 2012050984 W FR2012050984 W FR 2012050984W WO 2012153040 A1 WO2012153040 A1 WO 2012153040A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- chimney
- washer
- flange
- combustion chamber
- spark plug
- Prior art date
Links
Classifications
-
- 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
-
- 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
- F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
-
- 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
- F02C7/26—Starting; Ignition
- F02C7/264—Ignition
- F02C7/266—Electric
-
- 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
- F23R3/60—Support structures; Attaching or mounting means
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/35—Combustors or associated equipment
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/99—Ignition, e.g. ignition by warming up of fuel or oxidizer in a resonant acoustic cavity
-
- 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
- F23R2900/00005—Preventing fatigue failures or reducing mechanical stress in gas turbine components
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/00012—Details of sealing devices
Definitions
- the present invention relates to the general field of ignition systems of a gas turbine engine combustion chamber. It is more specifically a device for mounting a spark plug on a combustion chamber wall.
- the combustion chamber is generally made up of outer and inner longitudinal multiperforated walls and joined upstream by a transverse wall forming a chamber bottom. These longitudinal walls are fixed downstream on annular housings and define therewith an annular space receiving air from the compressor.
- the chamber bottom is traversed by a plurality of fuel injectors. Part of the air from the compressor is introduced into the combustion chamber at the injectors, mixed with the fuel and then burned in the chamber.
- Ignition of the combustion chamber is provided by means of one or two candles disposed downstream of the injectors. These spark plugs are typically attached to the outer casing and have their free end which passes through the outer wall of the combustion chamber. At this free end, each candle is more precisely mounted on the outer wall of the chamber by means of a mounting device allowing relative movements that can exist between the casing and the wall of the combustion chamber on which the candle is mounted.
- this type of mounting device consists of a chimney welded to the outer wall of the combustion chamber, and a candle guide receiving the free end of the candle and mounted floating inside the chimney so as to allow relative movements between the housing and the wall of the chamber.
- a candle guide receiving the free end of the candle and mounted floating inside the chimney so as to allow relative movements between the housing and the wall of the chamber.
- the present invention therefore has the main purpose of meeting such a need by proposing a device for mounting a spark plug in a combustion chamber of a gas turbine engine, comprising a chimney having a cylinder shape of axis XX and whose first axial end is intended to be fixed on a wall of a combustion chamber, said chimney comprising a flange extending radially inwards and centered on the axis XX, a washer fixed on a second axial end of the chimney opposite the first end so as to project inwardly of said chimney, and a sleeve forming a spark plug guide and comprising an inner flange and an outer flange axially spaced from each other by a portion substantially cylindrical and each extending radially outward, said sleeve being mounted floating inside the chimney with its flanges positi axially between the flange of the chimney and the washer, the inner flange being intended in operation to bear against the flange of the chimney and the outer flange having an outer
- the inner flange of the candle guide bears against the flange of the chimney, thereby sealing the device.
- the guide candle can not leave the chimney given the presence of the washer.
- the guide candle can move radially inside the space defined between the collar of the chimney and the washer, which allows to allow relative movements that may exist between the outer casing and the outer wall of the combustion chamber on which the device is mounted.
- Such a device is remarkable in particular that the shape and assembly of its components allows for an assembly having a small footprint in height, while allowing the introduction of cylindrical protectors around the chimney to avoid to damage it during laser multiperforation operations of the walls of the chamber.
- the cylindrical portion of the sleeve comprises a plurality of impact holes opening into the space defined between the flange of the chimney and the washer and opening towards the inside of said sleeve.
- Such holes provide cooling by impact of the free end of the candle.
- the washer advantageously comprises radial openings to allow air to enter the space defined between the flange of the chimney and the washer.
- These radial openings of the washer may be in the form of cuts made at the inner periphery of the washer and regularly distributed over the entire circumference thereof. The cuts are for example five in number.
- the distance radially separating the inside of the washer from the bushing is greater than the distance radially separating the inside of the chimney from the end of the flanges of the bushing. Any contact between the washer and the spark plug guide can thus be avoided so as to prevent any premature wear of the spark plug guide.
- the outer diameter of the inner collar of the sleeve is greater than the inner diameter of the flange of the chimney.
- the invention also relates to a gas turbine engine combustion chamber comprising at least one spark plug mounted on one of its walls by means of a device as defined above.
- the invention further relates to a gas turbine engine comprising such a combustion chamber.
- FIG. 1 is a schematic longitudinal sectional view of a combustion chamber equipped with a device according to the invention
- FIG. 2 is an enlarged view of the device of FIG. 1; and FIG. 3 is a perspective and exploded view of the device of FIGS. 1 and 2.
- the invention applies to any type of gas turbine engine combustion chamber, and in particular to a turbomachine annular combustion chamber such as that shown in FIG.
- the combustion chamber 10 is mounted inside an annular space 12 formed between an outer annular casing 14 and an inner annular casing 16 centered on the longitudinal axis 18 of the turbomachine.
- the annular space 12 in which the combustion chamber is mounted receives compressed air from a compressor of the turbomachine through an annular diffusion duct 20. This compressed air is in particular intended to ensure the combustion of the fuel. inside the room 10.
- Injection systems 22 distributed around the longitudinal axis 18 open into this annular space 12. These injection systems are each provided with a fuel injection nozzle 24 fixed to the outer casing 14.
- the combustion chamber 10 is formed of an outer annular wall 26 and an inner annular wall 28 centered on the longitudinal axis 18 of the turbomachine and each provided with multiperforation holes 29. At their downstream end, these walls are fixed on the casings 14, 16 delimiting the annular space 12. At their upstream end, these walls are interconnected by a transverse wall 30 forming bedroom background. The latter comprises a plurality of openings 32 for the passage of the fuel injection nozzles 24.
- At least one ignition system 34 of the combustion chamber is also provided.
- Each of these systems comprises in particular a spark plug 36 fixed to the outer casing 14 downstream of the injection systems 22. The free end of these spark plugs passes through the outer wall 26 of the combustion chamber to lead to inside of it.
- Each spark plug 36 is more precisely mounted on the outer wall 26 of the combustion chamber by means of a mounting device 100 according to the invention.
- the mounting device 100 is particularly shown in more detail in Figures 2 and 3. It comprises a chimney 200, a washer (or cup) 300 and a sleeve 400 forming a spark plug. All his pieces are of revolution.
- the chimney 200 has a hollow cylinder shape with an axis of revolution XX and having two axial ends 202, 204.
- a first axial end 202 is intended to be fixed (for example by welding) on the outer wall 26 of the combustion chamber. at a circular opening 38 formed therein.
- the second end 204 is free. Between its two ends is formed a flange 206 extending radially inwardly of the chimney and centered on the axis X-X.
- the washer 300 has a flat crown shape which is fixed (for example by welding) on the second axial end 204 of the chimney 200 so as to also project radially inwardly of said chimney.
- the washer comprises radial openings 302 made at its inner periphery. These openings allow the air outside the combustion chamber to cool the free end of the spark plug as described later. As shown in Figure 3, there are for example five in number and can be cutouts regularly performed on the entire inner circumference of the washer.
- the sleeve 400 forming a spark plug comprises an internal flange 402 positioned at a first axial end and a outer flange 404 spaced axially from the inner flange by a substantially cylindrical portion 406.
- This cylinder portion has over its entire circumference a plurality of impact holes 408 opening towards the inside of the candle guide.
- the collars they are substantially flat and each extend radially outwardly.
- the candle guide At its second radial end, the candle guide comprises a portion 410 flaring outwardly.
- the assembly of these different parts is as follows.
- the chimney 200 is first fixed on the outer wall 26 of the combustion chamber at its first axial end 202.
- the spark plug 400 is then mounted floating inside the chimney with its inner flange 402 bearing against the flange 206 of the chimney.
- the washer 300 is then fixed on the second axial end 204 of the chimney so as to trap the two flanges 402, 404 of the spark plug guide in an annular space 208 defined inside the chimney and delimited axially by the flange 206 of the fireplace and washer 300.
- the total space of the mounting device of the spark plug on the outer wall of the combustion chamber can be greatly reduced.
- the total height H of the device may be of the order of 10 mm, compared with a size of 15 mm for a device of the prior art.
- the device according to the invention is thus perfectly integrable in an environment where the distance between the outer wall of the combustion chamber and the outer casing surrounding it is reduced.
- the outer shape of this device being generally cylindrical, it is easy to position around it a protector 500 (see Figure 2) of cylindrical shape to laser by the multiperforation of the outer wall 26 of the chamber of combustion without damaging the chimney of the device.
- a protector 500 see Figure 2 of cylindrical shape to laser by the multiperforation of the outer wall 26 of the chamber of combustion without damaging the chimney of the device.
- the minimum height of such a protector is of the order of 5mm.
- the operation of the device once assembled is as follows.
- the free end of the spark plug 36 is brought inside the candle guide 400, the flared shape of its portion 410 to facilitate this assembly.
- the differential pressure existing between the inside and the outside of the chamber allows to "flatten" the spark plug guide, and more precisely its inner flange 402 against the flange 206 of the chimney, thus ensuring a perfect airtightness.
- the free end of the spark plug is impact-cooled in the following manner.
- the compressed air flowing between the outer casing and the outer wall of the combustion chamber enters the space 208 inside the chimney through the openings 302 made in the washer.
- the impact holes 408 made in the cylindrical portion of the spark plug guide open into this space and open inside the plug guide, so as to provide cooling by impact of the free end of the spark plug.
- openings 302 formed in the washer are dimensioned and positioned so that their total passage section is always greater than the total passage section of the impact holes 408 of the guide plug, and whatever the position of the candle guide in relation to the washer.
- the outer flange 404 of the spark plug guide 400 has an outer diameter d1 which is greater than the inner diameter d2 of the washer 300 so as to prevent in operation that the guide plug leaves the chimney.
- the outer diameter d3 of the inner flange 402 of the spark plug must be greater than the inside diameter d4 of the flange 206 of the chimney.
- the distance d5 radially separating the inside of the washer 300 from the portion facing the candle guide 400 is greater than the distance d6 radially separating the inside of the chimney 200 from the end of the flanges 402, 404 of the the socket (and in particular the largest of these collars).
- Any contact between the washer and the spark plug guide can: thus be avoided in operation so as to prevent any premature wear of the spark plug guide.
- it may be provided means for providing anti-rotation of the spark plug guide 400 relative to the chimney 200 so as to prevent the spark plug guide wear friction by the spark plug.
- the spark plug guide may for example have an internal lug abutting against a lug complementary to the chimney.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Cylinder Crankcases Of Internal Combustion Engines (AREA)
- Spark Plugs (AREA)
Abstract
Description
Claims
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US14/116,807 US9784186B2 (en) | 2011-05-10 | 2012-05-03 | Device for mounting a spark plug in a combustion engine of a gas turbine engine |
GB1319802.3A GB2508513B (en) | 2011-05-10 | 2012-05-03 | Device for mounting a spark plug in a combustion engine of a gas turbine engine |
US15/391,578 US10247101B2 (en) | 2011-05-10 | 2016-12-27 | Device for mounting a spark plug in a combustion engine of a gas turbine engine |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1154018 | 2011-05-10 | ||
FR1154018A FR2975172B1 (fr) | 2011-05-10 | 2011-05-10 | Dispositif pour le montage d'une bougie d'allumage dans une chambre de combustion de moteur a turbine a gaz |
Related Child Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US14/116,807 A-371-Of-International US9784186B2 (en) | 2011-05-10 | 2012-05-03 | Device for mounting a spark plug in a combustion engine of a gas turbine engine |
US15/391,578 Division US10247101B2 (en) | 2011-05-10 | 2016-12-27 | Device for mounting a spark plug in a combustion engine of a gas turbine engine |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2012153040A1 true WO2012153040A1 (fr) | 2012-11-15 |
Family
ID=46201715
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2012/050984 WO2012153040A1 (fr) | 2011-05-10 | 2012-05-03 | Dispositif pour le montage d'une bougie d'allumage dans une chambre de combustion de moteur a turbine a gaz |
Country Status (4)
Country | Link |
---|---|
US (2) | US9784186B2 (fr) |
FR (1) | FR2975172B1 (fr) |
GB (2) | GB2525535B (fr) |
WO (1) | WO2012153040A1 (fr) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP3018418A1 (fr) * | 2014-11-07 | 2016-05-11 | United Technologies Corporation | Corps d'ouverture de la paroi d'une chambre de combustion avec circuit de refroidissement |
FR3030741A1 (fr) * | 2014-12-23 | 2016-06-24 | Snecma | Ensemble a guide-bougie pour banc d'essai |
Families Citing this family (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2953908A1 (fr) * | 2009-12-16 | 2011-06-17 | Snecma | Guidage d'une bougie dans une chambre de combustion de turbomachine |
US9989254B2 (en) * | 2013-06-03 | 2018-06-05 | General Electric Company | Combustor leakage control system |
US10502422B2 (en) | 2013-12-05 | 2019-12-10 | United Technologies Corporation | Cooling a quench aperture body of a combustor wall |
FR3015642B1 (fr) * | 2013-12-23 | 2018-03-02 | Safran Aircraft Engines | Bougie de turbomachine et son dispositif de fixation radiale |
US10156189B2 (en) * | 2014-01-28 | 2018-12-18 | Pratt & Whitney Canada Corp. | Combustor igniter assembly |
US20180030899A1 (en) * | 2016-07-27 | 2018-02-01 | Honda Motor Co., Ltd. | Structure for supporting spark plug for gas turbine engine |
US10767557B1 (en) | 2017-03-10 | 2020-09-08 | Ladan Behnia | Gas-assisted air turbine system for generating electricity |
US20190234310A1 (en) * | 2018-01-29 | 2019-08-01 | Pratt & Whitney Canada Corp. | Segmented internal fuel manifold |
FR3083264B1 (fr) * | 2018-06-29 | 2021-06-18 | Safran Aircraft Engines | Dispositif de guidage dans une chambre de combustion |
FR3096114B1 (fr) * | 2019-05-13 | 2022-10-28 | Safran Aircraft Engines | Chambre de combustion comprenant des moyens de refroidissement d’une zone d’enveloppe annulaire en aval d’une cheminée |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB638283A (en) * | 1947-02-10 | 1950-06-07 | Rolls Royce | Improvements relating to gas sealing joints |
US4275559A (en) * | 1979-08-31 | 1981-06-30 | General Electric Company | Retractable igniter device for gas turbines |
EP1975512A2 (fr) * | 2007-03-30 | 2008-10-01 | Honeywell International Inc. | Chambres de combustion dotées d'allumeurs refroidis par projection et tubes d'allumeur pour un refroidissement amélioré d'allumeurs |
FR2926329A1 (fr) * | 2008-01-15 | 2009-07-17 | Snecma Sa | Agencement d'une bougie du type a semi-conducteur dans une chambre de combustion de moteur a turbine a gaz. |
FR2927367A1 (fr) | 2008-02-11 | 2009-08-14 | Snecma Sa | Dispositif de montage d'une bougie d'allumage dans une chambre de combustion de moteur a turbine a gaz |
-
2011
- 2011-05-10 FR FR1154018A patent/FR2975172B1/fr active Active
-
2012
- 2012-05-03 US US14/116,807 patent/US9784186B2/en active Active
- 2012-05-03 WO PCT/FR2012/050984 patent/WO2012153040A1/fr active Application Filing
- 2012-05-03 GB GB1514102.1A patent/GB2525535B/en active Active
- 2012-05-03 GB GB1319802.3A patent/GB2508513B/en active Active
-
2016
- 2016-12-27 US US15/391,578 patent/US10247101B2/en active Active
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB638283A (en) * | 1947-02-10 | 1950-06-07 | Rolls Royce | Improvements relating to gas sealing joints |
US4275559A (en) * | 1979-08-31 | 1981-06-30 | General Electric Company | Retractable igniter device for gas turbines |
EP1975512A2 (fr) * | 2007-03-30 | 2008-10-01 | Honeywell International Inc. | Chambres de combustion dotées d'allumeurs refroidis par projection et tubes d'allumeur pour un refroidissement amélioré d'allumeurs |
FR2926329A1 (fr) * | 2008-01-15 | 2009-07-17 | Snecma Sa | Agencement d'une bougie du type a semi-conducteur dans une chambre de combustion de moteur a turbine a gaz. |
FR2927367A1 (fr) | 2008-02-11 | 2009-08-14 | Snecma Sa | Dispositif de montage d'une bougie d'allumage dans une chambre de combustion de moteur a turbine a gaz |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP3018418A1 (fr) * | 2014-11-07 | 2016-05-11 | United Technologies Corporation | Corps d'ouverture de la paroi d'une chambre de combustion avec circuit de refroidissement |
FR3030741A1 (fr) * | 2014-12-23 | 2016-06-24 | Snecma | Ensemble a guide-bougie pour banc d'essai |
Also Published As
Publication number | Publication date |
---|---|
GB2508513A (en) | 2014-06-04 |
US10247101B2 (en) | 2019-04-02 |
GB201514102D0 (en) | 2015-09-23 |
GB2508513B (en) | 2015-10-07 |
GB2525535A (en) | 2015-10-28 |
FR2975172A1 (fr) | 2012-11-16 |
FR2975172B1 (fr) | 2013-05-31 |
US20170108225A1 (en) | 2017-04-20 |
US20140137568A1 (en) | 2014-05-22 |
GB2525535B (en) | 2016-01-27 |
GB201319802D0 (en) | 2013-12-25 |
US9784186B2 (en) | 2017-10-10 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
WO2012153040A1 (fr) | Dispositif pour le montage d'une bougie d'allumage dans une chambre de combustion de moteur a turbine a gaz | |
CA2592788C (fr) | Agencement a liaison par crabot pour chambre de combustion de turbomachine | |
EP2088374B1 (fr) | Dispositif de montage d'une bougie d'allumage dans une chambre de combustion de moteur à turbine à gaz | |
EP3247946B1 (fr) | Agencement pour une chambre de combustion de turbomachine d'aéronef | |
WO2011061143A1 (fr) | Chambre de combustion avec bougie d'allumage ventilee | |
FR2871844A1 (fr) | Montage etanche d'un distributeur de turbine haute pression sur une extremite d'une chambre de combustion dans une turbine a gaz | |
WO2014053728A1 (fr) | Chambre de combustion comprenant un tube à flamme fixé au moyen de trois éléments de centrage | |
CA2886298C (fr) | Ensemble de combustion de turbomachine a variation d'alimentation d'air | |
EP3277542A1 (fr) | Ensemble pour le passage d'un harnais electrique dans une turbomachine | |
FR3013805A1 (fr) | Ensemble de combustion a acces facilite des cannes de prevaporisation. | |
CA2582624C (fr) | Bras accroche-flammes d'une chambre de post-combustion | |
FR3026827B1 (fr) | Chambre de combustion de turbomachine | |
CA2891076C (fr) | Support de tube d'evacuation d'air dans une turbomachine | |
WO2012022873A2 (fr) | Systeme d'injection de carburant pour turbo-reacteur et procede d'assemblage d'un tel systeme d'injection | |
EP3575689A1 (fr) | Module de combustion de turbomachine a gaz avec butee de fond de chambre | |
EP3928034B1 (fr) | Chambre de combustion pour une turbomachine | |
WO2017013326A1 (fr) | Étage d'aubes a calage variable pour une turbomachine, turbomachine et procédé de montage associé | |
FR2952704A1 (fr) | Guidage rotulant d'une bougie d'allumage dans une chambre de combustion d'une turbomachine | |
FR3071908A1 (fr) | Chambre de combustion de turbomachine a geometrie de cheminee fixe | |
EP3969813B1 (fr) | Chambre de combustion comprenant des moyens de refroidissement d'une zone d'enveloppe annulaire en aval d'une cheminée | |
FR3015641A1 (fr) | Dispositif d'injection dans une turbomachine | |
FR3093243A1 (fr) | Corps semi-conducteur pour une bougie d’allumage de turbomachine | |
FR3129988A1 (fr) | Tuyere d’echappement de gaz de combustion pour une turbomachine d’aeronef | |
FR3129987A1 (fr) | Tuyere d’echappement de gaz de combustion pour une turbomachine d’aeronef | |
FR3093344A1 (fr) | Ensemble pour une turbine de turbomachine |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
121 | Ep: the epo has been informed by wipo that ep was designated in this application |
Ref document number: 12725092 Country of ref document: EP Kind code of ref document: A1 |
|
ENP | Entry into the national phase |
Ref document number: 1319802 Country of ref document: GB Kind code of ref document: A Free format text: PCT FILING DATE = 20120503 |
|
NENP | Non-entry into the national phase |
Ref country code: DE |
|
WWE | Wipo information: entry into national phase |
Ref document number: 1319802.3 Country of ref document: GB |
|
WWE | Wipo information: entry into national phase |
Ref document number: 14116807 Country of ref document: US |
|
122 | Ep: pct application non-entry in european phase |
Ref document number: 12725092 Country of ref document: EP Kind code of ref document: A1 |