EP0461026A1 - Fuel injection assembly for turbomachine, including preevaporation chamber - Google Patents
Fuel injection assembly for turbomachine, including preevaporation chamber Download PDFInfo
- Publication number
- EP0461026A1 EP0461026A1 EP91401458A EP91401458A EP0461026A1 EP 0461026 A1 EP0461026 A1 EP 0461026A1 EP 91401458 A EP91401458 A EP 91401458A EP 91401458 A EP91401458 A EP 91401458A EP 0461026 A1 EP0461026 A1 EP 0461026A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- bowl
- wall
- chamber
- combustion chamber
- vaporization
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
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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
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
-
- 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
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/30—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/21—Finger-ring forming or sizing
Definitions
- the present invention relates to the mounting of combustion chambers of turbomachines.
- turbomachinery in particular aviation turbojets, are equipped with annular combustion chambers and comprise, arranged between the fuel injectors and the combustion chamber proper, fuel pre-vaporization bowls.
- pre-vaporization bowls are mounted mobile in their housing, this to take account of the significant relative movements which occur in operation between injectors and chambers.
- the bowls must therefore be mounted floating radially with respect to the chamber and axially with respect to the injectors.
- turbojet engines are designed in a modular way and the assembly sequence of the combustion chambers is carried out by assembling the chamber equipped with its spraying bowls, inside the chamber casing, itself equipped of its injectors. This assembly is carried out with the engine in a horizontal position.
- the radial mobility of the bowls relative to the chamber means that they take by gravity, a low position eccentric by several millimeters relative to their theoretical axis.
- the present invention aims to avoid this type of risk during assembly while retaining the bowls the possibility of sliding radially in their housing and absorbing in operation the relative movements between chamber and injectors.
- the invention therefore relates to a fuel injection assembly inside a turbomachine combustion chamber, mounted on the wall delimiting said chamber and comprising a spray bowl mounted floating relative to the wall of the combustion chamber, parallel to a determined direction.
- a part of a structure integral with the pre-vaporization bowl and a part integral with the wall of the combustion chamber are aligned substantially parallel to said determined direction, and are capable of being arranged at a variable distance l 'from one another, however, that at least one magnet is fixed on one of said parts and is able to cooperate with the other part to fix it or, on the contrary, detach from it, in the first case, now in position the pre-vaporization bowl relative to the combustion chamber, and, in the second case, leaving said pre-vaporization bowl free to float relative to said part of the wall of the combustion chamber.
- FIG. 1 represents an annular combustion chamber, the inner 1 and outer 2 walls of which appear.
- a circular opening 4 On the dome 3 of the chamber bottom is pierced a circular opening 4 inside which is fixed a circular support flange 5 comprising a cylindrical downstream part 5a, welded externally inside the opening 4, and a cylindrical upstream part 5b inside which a stop ring 6 is mounted, the two cylindrical parts 5a and 5b of different diameters being connected by a central central part 5c.
- the pre-vaporization bowl 7 has an internal ferrule 7a and an external ferrule 7b, separated upstream by fins 8 forming a swirl swirl for the pre-vaporization air.
- the two ferrules 7a and 7b form a frustoconical passage 7c downstream of which the ferrule 7b flares in frustoconical veil 7d forming the bowl proper.
- a cylindrical outer wall 7e is welded to the downstream edge of this veil 7d.
- a mounting ring 9 On the outer edge of the 7th wall is welded a mounting ring 9 whose cross section is square.
- the ferrule therefore comprises a cylindrical part 9a and a flat part 9b.
- a tongue 9c extends radially on the outer edge of the flat part 9b of the mounting ring 9.
- the tongue passes through a notch 5d of the cylindrical part 5b of the support flange so that the bowl can slide radially along the axis XX ′ of the support flange, said axis being coincident with the diameter of the chamber which carries the center 0 of the bowl.
- the stop ring 6 is then welded inside the support flange 5 so that the only clearance left at the ferrule 9 and therefore to the bowl 7 is a radial clearance.
- Such a combustion chamber comprising pre-spraying bowls regularly distributed over its circumference has the support flanges of its bowls oriented so that their tongues 9c as well as the direction of action of the force exerted by the elastic means are radial.
- the injector 11 is mounted without radial play, but floating axially inside the internal ferrule 7a of the bowl 7.
- a permanent magnet 15 is fixed, on the underside of said intersection of the cylindrical part 5b.
- This magnet is placed above a magnetizable patch 12, itself fixed on the upper face of the upper intersection of the cylindrical outer wall 7e of the pre-vaporization bowl with the diameter XX ′.
- the fixings of the permanent magnet 15 and of the magnetizable patch 12 are produced by welding 13 on the respective parts.
- the magnetizable patch 12 and the permanent magnet 15 are arranged opposite one another, either at close mutual distance (FIGS. 1 and 2), or magnetically bonded to each other (FIGS. 3 and 4) .
- the material of the magnetizable patch is "Z12C13" (AFNOR standard).
- the pre-vaporization bowl 7 is suspended from the permanent magnet 15 in the configuration of FIGS. 3 and 4, which avoids the direct support of the pre-vaporization bowl by the nose 14 of the injector 11, and protects said constraint injector corresponding.
- the nose 14 of the injector 11 then has the possibility of moving freely relative to the pre-spray bowl 17 in the direction of the axis 16.
- the permanent magnet 15 will remain ready to receive the magnetizable patch 12 and thus relieve the nose 14 of the injector again from the weight of the pre-vaporization bowl.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Fuel-Injection Apparatus (AREA)
- Spray-Type Burners (AREA)
Abstract
Description
La présente invention concerne le montage des chambres de combustion de turbomachines.The present invention relates to the mounting of combustion chambers of turbomachines.
La plupart des turbomachines actuelles, notamment les turboréacteurs d'aviation, sont équipées de chambres de combustion annulaires et comportent, disposés entre les injecteurs de carburant et la chambre de combustion proprement dite, des bols de prévaporisation de carburant.Most current turbomachinery, in particular aviation turbojets, are equipped with annular combustion chambers and comprise, arranged between the fuel injectors and the combustion chamber proper, fuel pre-vaporization bowls.
Un exemple de tels bols de prévaporisation est décrit dans le document FR-A-2 479 952.An example of such pre-vaporization bowls is described in document FR-A-2 479 952.
Ces bols de prévaporisation sont montés mobiles dans leur logement, ceci pour tenir compte des mouvements relatifs importants qui se produisent en fonctionnement entre injecteurs et chambres.These pre-vaporization bowls are mounted mobile in their housing, this to take account of the significant relative movements which occur in operation between injectors and chambers.
Les bols doivent donc être montés flottants radialement par rapport à la chambre et axialement par rapport aux injecteurs.The bowls must therefore be mounted floating radially with respect to the chamber and axially with respect to the injectors.
D'autre part, les turboréacteurs actuels sont conçus de façon modulaire et la séquence de montage des chambres de combustion s'effectue par assemblage de la chambre équipée de ses bols de prévaporisation, à l'intérieur du carter de chambre, lui-même équipé de ses injecteurs. Cet assemblage s'effectue, moteur en position horizontale.On the other hand, current turbojet engines are designed in a modular way and the assembly sequence of the combustion chambers is carried out by assembling the chamber equipped with its spraying bowls, inside the chamber casing, itself equipped of its injectors. This assembly is carried out with the engine in a horizontal position.
Or dans cette position, la mobilité radiale des bols par rapport à la chambre fait que ceux-ci prennent par gravité, une position basse excentrée de plusieurs millimètres par rapport à leur axe théorique.However, in this position, the radial mobility of the bowls relative to the chamber means that they take by gravity, a low position eccentric by several millimeters relative to their theoretical axis.
De ce fait, le risque existe, lors du centrage des bols sur leurs injecteurs respectifs, de soumettre ces derniers à des contraintes inacceptables.Therefore, the risk exists, when centering the bowls on their respective injectors, subjecting them to unacceptable stresses.
La présente invention a pour but d'éviter ce type de risques lors du montage tout en conservant aux bols la possibilité de coulisser radialement dans leur logement et d'absorber en fonctionnement les mouvements relatifs entre chambre et injecteurs.The present invention aims to avoid this type of risk during assembly while retaining the bowls the possibility of sliding radially in their housing and absorbing in operation the relative movements between chamber and injectors.
L'invention a donc pour objet un ensemble d'injection de carburant à l'intérieur d'une chambre de combustion de turbomachine, monté sur la paroi délimitant ladite chambre et comprenant un bol de prévaporisation monté flottant par rapport à la paroi de la chambre de combustion, parallélement à une direction déterminée.The invention therefore relates to a fuel injection assembly inside a turbomachine combustion chamber, mounted on the wall delimiting said chamber and comprising a spray bowl mounted floating relative to the wall of the combustion chamber, parallel to a determined direction.
Selon l'invention, une partie d'une structure solidaire du bol de prévaporisation et une partie solidaire de la paroi de la chambre de combustion sont alignées sensiblement parallèlement à ladite direction déterminée, et, sont susceptibles d'être disposées à une distance variable l'une de l'autre, cependant qu'un aimant au moins est fixé sur l'une desdites parties et est apte à coopérer avec l'autre partie pour s'y fixer ou au contraire s'en détacher, dans le premier cas, maintenant en position le bol de prévaporisation par rapport à la chambre de combustion, et, dans le deuxième cas, laissant ledit bol de prévaporisation libre de flotter par rapport à ladite partie de la paroi de la chambre de combustion.According to the invention, a part of a structure integral with the pre-vaporization bowl and a part integral with the wall of the combustion chamber are aligned substantially parallel to said determined direction, and are capable of being arranged at a variable distance l 'from one another, however, that at least one magnet is fixed on one of said parts and is able to cooperate with the other part to fix it or, on the contrary, detach from it, in the first case, now in position the pre-vaporization bowl relative to the combustion chamber, and, in the second case, leaving said pre-vaporization bowl free to float relative to said part of the wall of the combustion chamber.
Les avantageuses dispositions suivantes sont, en outre, de préférence adoptées :
- la partie de la structure solidaire du bol de prévaporisation est disposée à la partie supérieure dudit bol et en dessous de la partie solidaire de la paroi de la chambre de combustion, de manière que, dans la configuration de fixation dudit au moins un aimant sur la partie complémentaire de celle sur laquelle il est monté, ledit bol de prévaporisation soit suspendu à la paroi de la chambre de combustion ;
- une pastille magnétisable est fixée sur la partie complémentaire de celle sur laquelle est fixé l'aimant ;
- le ou les aimants sont des aimants permanents.
- the part of the structure integral with the pre-vaporization bowl is disposed at the top of said bowl and below the part integral with the wall of the combustion chamber, so that, in the configuration for fixing said at least one magnet to the part complementary to that on which it is mounted, said pre-vaporization bowl is suspended from the wall of the combustion chamber;
- a magnetizable patch is fixed on the part complementary to that on which the magnet is fixed;
- the magnet (s) are permanent magnets.
L'invention sera mieux comprise, et des caractéristiques secondaires et leurs avantages apparaîtront au cours de la description d'une réalisation donnée ci-dessous à titre d'exemple.The invention will be better understood, and secondary characteristics and their advantages will appear during the description of an embodiment given below by way of example.
Il est entendu que la description et les dessins ne sont donnés qu'à titre indicatif et non limitatif.It is understood that the description and the drawings are given for information only and are not limiting.
Il sera fait référence aux dessins annexés, dans lesquels :
- la figure 1 est une coupe longitudinale d'une chambre de combustion annulaire, la coupe étant effectuée au droit d'un dispositif d'injection dans une position du bol centrée par rapport à l'injecteur après montage ;
- la figure 2 est une coupe selon II-II de la figure 1 de la bride support, de la virole et du dispositif de montage conformes à l'invention ;
- les figures 3 et 4 sont des coupes similaires à celles des figures 1 et 2, dans lesquelles le bol, au moment du montage, est décentré radialement vers l'extérieur de la chambre.
- Figure 1 is a longitudinal section of an annular combustion chamber, the cut being made in line with an injection device in a position of the bowl centered relative to to the injector after assembly;
- Figure 2 is a section on II-II of Figure 1 of the support flange, the ferrule and the mounting device according to the invention;
- Figures 3 and 4 are sections similar to those of Figures 1 and 2, in which the bowl, at the time of assembly, is offset radially outward from the chamber.
La figure 1 représente une chambre de combustion annulaire, dont apparaissent les parois interne 1 et externe 2. Sur le dôme 3 de fond de chambre est percée une ouverture circulaire 4 à l'intérieur de laquelle est fixée une bride-support 5 circulaire comportant une partie aval cylindrique 5a, soudée extérieurement à l'intérieur de l'ouverture 4, et une partie amont 5b cylindrique à l'intérieur de laquelle est montée une bague d'arrêt 6, les deux parties cylindriques 5a et 5b de diamètres différents étant reliées par une partie centrale 5c plane.FIG. 1 represents an annular combustion chamber, the inner 1 and outer 2 walls of which appear. On the
Le bol de prévaporisation 7 comporte une virole interne 7a et une virole externe 7b, séparées en amont par des ailettes 8 formant une vrille de turbulence pour l'air de prévaporisation. Les deux viroles 7a et 7b forment un passage tronconique 7c en aval duquel la virole 7b s'évase en voile tronconique 7d formant le bol proprement dit.The
Une paroi externe cylindrique 7e est soudée au bord aval de ce voile 7d. Sur le bord externe de la paroi 7e est soudée une virole de montage 9 dont la section droite est en équerre. La virole comporte donc une partie cylindrique 9a et une partie plane 9b.A cylindrical
Une languette 9c s'étend radialement sur le bord externe de la partie plane 9b de la virole de montage 9. La languette traverse une encoche 5d de la partie cylindrique 5b de la bride support de telle sorte que le bol peut coulisser radialement le long de l'axe XX′ de la bride support, ledit axe étant confondu avec le diamètre de la chambre qui porte le centre 0 du bol.A
Lorsque le bol 7 équipé de sa virole 9 est monté dans la bride support, la bague d'arrêt 6 est alors soudée à l'intérieur de la bride support 5 de telle sorte que le seul jeu laissé à la virole 9 et donc au bol 7 est un jeu radial.When the
Une telle chambre de combustion comportant des bols de prévaporisation régulièrement répartis sur sa circonférence a les brides supports de ses bols orientées de telle sorte que leurs languettes 9c ainsi que la direction d'action de la force exercée par les moyens élastiques soient radiales.Such a combustion chamber comprising pre-spraying bowls regularly distributed over its circumference has the support flanges of its bowls oriented so that their
L'injecteur 11 est monté sans jeu radial, mais flottant axialement à l'intérieur de la virole interne 7a du bol 7.The
A l'intersection supérieure de la partie cylindrique 5b de la bride support 5 avec le diamètre XX′, un aimant permanent 15 est fixé, sur la face inférieure de ladite intersection de la partie cylindrique 5b. Cet aimant est disposé au-dessus d'une pastille magnétisable 12, elle-même fixée sur la face supérieure de l'intersection supérieure de la paroi externe cylindrique 7e du bol de prévaporisation avec le diamètre XX′. Les fixations de l'aimant permanent 15 et de la pastille magnétisable 12 sont réalisées par soudage 13 sur les pièces respectives.At the upper intersection of the
La pastille magnétisable 12 et l'aimant permanent 15 sont disposés en regard l'un de l'autre, soit à faible distance mutuelle (figures 1 et 2), soit collés magnétiquement l'un sur l'autre (figures 3 et 4).The
Pour le matériau de l'aimant permanent, le choix s'est porté sur un alliage anisotrope, le "TICONAL M" de la Société "GIFFEY-PRETRE" dont les caractéristiques magnétiques sont compatibles avec les conditions de fonctionnement notamment en température. En effet, celle-ci de 650°C est inférieure au point de Curie de cet alliage (860°C) bien qu'au-dessus de la température de changement de structure (550°C), ce qui conduit à une faible perte d'aimantation, de l'ordre de 2 %.For the material of the permanent magnet, the choice fell on an anisotropic alloy, the "TICONAL M" of the Company "GIFFEY-PRETRE" whose magnetic characteristics are compatible with the operating conditions in particular in temperature. Indeed, this one of 650 ° C is lower than the Curie point of this alloy (860 ° C) although above the temperature of change of structure (550 ° C), which leads to a low loss magnetization, of the order of 2%.
Pour la fermeture du flux, le matériau de la pastille magnétisable est du "Z12C13" (norme AFNOR).For closing the flow, the material of the magnetizable patch is "Z12C13" (AFNOR standard).
Au moment du montage, le bol de prévaporisation 7 est suspendu à l'aimant permanent 15 dans la configuration des figures 3 et 4, ce qui évite le support direct du bol de prévaporisation par le nez 14 de l'injecteur 11, et protège ledit injecteur des contraintes correspondantes.At the time of assembly, the
Pendant le fonctionnement de la chambre de combustion, après montage définitif du bol de prévaporisation 7, celui-ci est centré par rapport à l'axe 16 du nez 14 de l'injecteur (figures 1 et 2), et la force de suspension du bol de prévaporisation 7 par l'aimant permanent 15 est devenue inférieure aux efforts du montage, de sorte que la pastille magnétisable 12 a été détachée de l'aimant permanent 15.During the operation of the combustion chamber, after final assembly of the
Le nez 14 de l'injecteur 11 a alors la possibilité de se mouvoir librement par rapport au bol de prévaporisation 17 dans le sens de l'axe 16.The
Au moment d'un démontage ultérieur, l'aimant permanent 15 restera prêt à recevoir la pastille magnétisable 12 et à soulager ainsi de nouveau le nez 14 de l'injecteur du poids du bol de prévaporisation.At the time of subsequent disassembly, the
L'invention n'est pas limitée à la réalisation représentée, mais en couvre au contraire toutes les variantes qui pourraient lui être apportées sans sortir de son cadre, ni de son esprit.The invention is not limited to the embodiment shown, but on the contrary covers all the variants which could be made to it without departing from its scope or its spirit.
Claims (4)
caractérisé en ce qu'une partie (7e) d'une structure solidaire du bol de prévaporisation (7) et une partie (5b) solidaire (3-4-5) de la paroi (1-2) de la chambre de combustion sont alignées sensiblement parallèlement à ladite direction déterminée (XX′), et, sont susceptibles d'être disposées à une distance variable l'une de l'autre, et en ce qu'un aimant (15) au moins est fixé sur l'une (5b) desdites parties et est apte à coopérer avec l'autre partie (7e) pour s'y fixer ou au contraire s'en détacher, dans le premier cas, maintenant en position le bol de prévaporisation (7) par rapport à la chambre de combustion, et, dans le deuxième cas, laissant ledit bol de prévaporisation (7) libre de flotter par rapport à ladite partie de la paroi de la chambre de combustion.Fuel injection assembly inside a turbomachine combustion chamber, mounted on the wall (1-2) delimiting said chamber and comprising a pre-vaporization bowl (7) mounted floating relative to the wall of the chamber combustion, parallel to a determined direction (XX ′),
characterized in that a part (7e) of a structure integral with the pre-vaporization bowl (7) and a part (5b) integral (3-4-5) with the wall (1-2) of the combustion chamber are aligned substantially parallel to said determined direction (XX ′), and are capable of being arranged at a variable distance from each other, and in that at least one magnet (15) is fixed to one (5b) of said parts and is able to cooperate with the other part (7e) to attach to it or, on the contrary, detach from it, in the first case, keeping the pre-spray bowl (7) in position relative to the combustion chamber, and, in the second case, leaving said pre-vaporization bowl (7) free to float relative to said part of the wall of the combustion chamber.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR9006947 | 1990-06-05 | ||
| FR9006947A FR2662784B1 (en) | 1990-06-05 | 1990-06-05 | INJECTION ASSEMBLY FOR A TURBOMACHINE, COMPRISING A PREVAPORIZATION BOWL. |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| EP0461026A1 true EP0461026A1 (en) | 1991-12-11 |
| EP0461026B1 EP0461026B1 (en) | 1993-07-28 |
Family
ID=9397268
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP91401458A Expired - Lifetime EP0461026B1 (en) | 1990-06-05 | 1991-06-05 | Fuel injection assembly for turbomachine, including preevaporation chamber |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US5172545A (en) |
| EP (1) | EP0461026B1 (en) |
| JP (1) | JP2578533B2 (en) |
| DE (1) | DE69100199T2 (en) |
| FR (1) | FR2662784B1 (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2956724A1 (en) * | 2010-02-23 | 2011-08-26 | Snecma | FUEL INJECTION SYSTEM FOR A TURBOMACHINE COMBUSTION CHAMBER |
| CN103047682A (en) * | 2012-12-27 | 2013-04-17 | 中国燃气涡轮研究院 | Partial pre-mixing and pre-evaporation burning chamber with prefilm type nozzle |
Families Citing this family (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5577379A (en) * | 1994-12-15 | 1996-11-26 | United Technologies Corporation | Fuel nozzle guide retainer assembly |
| US5961316A (en) * | 1995-10-25 | 1999-10-05 | Weil-Mclain | Oil burner |
| US7007480B2 (en) * | 2003-04-09 | 2006-03-07 | Honeywell International, Inc. | Multi-axial pivoting combustor liner in gas turbine engine |
| US6912782B2 (en) | 2003-04-09 | 2005-07-05 | Honeywell International Inc. | Forming and assembly method for multi-axial pivoting combustor liner in gas turbine engine |
| US7690207B2 (en) * | 2004-08-24 | 2010-04-06 | Pratt & Whitney Canada Corp. | Gas turbine floating collar arrangement |
| US7134286B2 (en) * | 2004-08-24 | 2006-11-14 | Pratt & Whitney Canada Corp. | Gas turbine floating collar arrangement |
| FR2885201B1 (en) * | 2005-04-28 | 2010-09-17 | Snecma Moteurs | EASILY DISMANTLING COMBUSTION CHAMBER WITH IMPROVED AERODYNAMIC PERFORMANCE |
| FR2893390B1 (en) * | 2005-11-15 | 2011-04-01 | Snecma | BOTTOM OF COMBUSTION CHAMBER WITH VENTILATION |
| US7926280B2 (en) * | 2007-05-16 | 2011-04-19 | Pratt & Whitney Canada Corp. | Interface between a combustor and fuel nozzle |
| US9291139B2 (en) | 2008-08-27 | 2016-03-22 | Woodward, Inc. | Dual action fuel injection nozzle |
| US20100186414A1 (en) * | 2008-12-15 | 2010-07-29 | Sonic Blue Aerospace, Inc. | Magnetic ion plasma annular injection combustor |
| DE102011014972A1 (en) * | 2011-03-24 | 2012-09-27 | Rolls-Royce Deutschland Ltd & Co Kg | Combustor head with brackets for seals on burners in gas turbines |
| FR3026827B1 (en) * | 2014-10-01 | 2019-06-07 | Safran Aircraft Engines | TURBOMACHINE COMBUSTION CHAMBER |
| GB2543803B (en) * | 2015-10-29 | 2019-10-30 | Rolls Royce Plc | A combustion chamber assembly |
| US20170227224A1 (en) * | 2016-02-09 | 2017-08-10 | Solar Turbines Incorporated | Fuel injector for combustion engine system, and engine operating method |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3273343A (en) * | 1965-03-08 | 1966-09-20 | Dickens Inc | Combustion chamber construction in gas turbine power plant |
| GB2073398A (en) * | 1980-04-02 | 1981-10-14 | United Technologies Corp | Fuel nozzle guide and seal for a gas turbine engine |
| EP0214393A1 (en) * | 1985-08-31 | 1987-03-18 | BBC Brown Boveri AG | Antivibration device for turbo machine blades |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2639095B1 (en) * | 1988-11-17 | 1990-12-21 | Snecma | COMBUSTION CHAMBER OF A TURBOMACHINE WITH FLOATING MOUNTS PREVAPORIZATION BOWLS |
-
1990
- 1990-06-05 FR FR9006947A patent/FR2662784B1/en not_active Expired - Lifetime
-
1991
- 1991-06-04 US US07/710,112 patent/US5172545A/en not_active Expired - Lifetime
- 1991-06-05 JP JP3160962A patent/JP2578533B2/en not_active Expired - Fee Related
- 1991-06-05 DE DE91401458T patent/DE69100199T2/en not_active Expired - Fee Related
- 1991-06-05 EP EP91401458A patent/EP0461026B1/en not_active Expired - Lifetime
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3273343A (en) * | 1965-03-08 | 1966-09-20 | Dickens Inc | Combustion chamber construction in gas turbine power plant |
| GB2073398A (en) * | 1980-04-02 | 1981-10-14 | United Technologies Corp | Fuel nozzle guide and seal for a gas turbine engine |
| EP0214393A1 (en) * | 1985-08-31 | 1987-03-18 | BBC Brown Boveri AG | Antivibration device for turbo machine blades |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2956724A1 (en) * | 2010-02-23 | 2011-08-26 | Snecma | FUEL INJECTION SYSTEM FOR A TURBOMACHINE COMBUSTION CHAMBER |
| US8453459B2 (en) | 2010-02-23 | 2013-06-04 | Snecma | Fuel injection system for a combustion chamber of a turbomachine |
| CN103047682A (en) * | 2012-12-27 | 2013-04-17 | 中国燃气涡轮研究院 | Partial pre-mixing and pre-evaporation burning chamber with prefilm type nozzle |
Also Published As
| Publication number | Publication date |
|---|---|
| FR2662784A1 (en) | 1991-12-06 |
| DE69100199T2 (en) | 1993-12-09 |
| US5172545A (en) | 1992-12-22 |
| DE69100199D1 (en) | 1993-09-02 |
| JPH04227412A (en) | 1992-08-17 |
| EP0461026B1 (en) | 1993-07-28 |
| FR2662784B1 (en) | 1992-08-14 |
| JP2578533B2 (en) | 1997-02-05 |
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