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EP4339515B1 - Buse de carburant - Google Patents

Buse de carburant Download PDF

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Publication number
EP4339515B1
EP4339515B1 EP23197278.7A EP23197278A EP4339515B1 EP 4339515 B1 EP4339515 B1 EP 4339515B1 EP 23197278 A EP23197278 A EP 23197278A EP 4339515 B1 EP4339515 B1 EP 4339515B1
Authority
EP
European Patent Office
Prior art keywords
stem
tip
flange
fuel nozzle
fuel
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.)
Active
Application number
EP23197278.7A
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German (de)
English (en)
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EP4339515A1 (fr
Inventor
Assaf Farah
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Pratt and Whitney Canada Corp
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Pratt and Whitney Canada Corp
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Pratt and Whitney Canada Corp filed Critical Pratt and Whitney Canada Corp
Publication of EP4339515A1 publication Critical patent/EP4339515A1/fr
Application granted granted Critical
Publication of EP4339515B1 publication Critical patent/EP4339515B1/fr
Active legal-status Critical Current
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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

Definitions

  • the application relates generally to turbine engines and, more particularly, to fuel nozzles for turbine engines.
  • the areas surrounding the combustor have elevated temperatures because of the heat generated by the combustor as fuel is combusted therein. Transfer of such thermal energy may influence the function of components surrounding the combustor, such as fuel nozzles.
  • the structures defining passages via which fuel flows inside fuel nozzles may require particular thermal management consideration.
  • US 6 076 356 A discloses a fuel injector with an internally heat-shielded nozzle.
  • a fuel nozzle for a turbine engine as claimed in claim 1.
  • first stem end and the second stem end are respectively joined to the flange and to the tip by brazing, welding or soldering.
  • first line end and the second line end are respectively fixedly joined to the flange and to the tip by brazing, welding or soldering.
  • the first stem end and the second stem end are respectively matingly received by the flange and the tip such that the stem chamber extends from inside the flange to inside the tip.
  • the first stem end and the second stem end are cylindrical in shape.
  • the stem has a constant wall thickness throughout a length thereof.
  • the peripheral wall has a thickness of between 0.89 mm and 1.52 mm at a location spaced away from the flange and from the tip.
  • an or the inner diameter of the peripheral wall is between 10.2 mm and 15.2 mm.
  • the stem has an opening defined in the peripheral wall at an intermediate location between the tip and the flange, the opening in fluid communication between the stem chamber and outside the fuel nozzle.
  • the opening is located closer to the flange than to the tip.
  • the opening has a cross-sectional area that is less than 0.6 mm 2 .
  • the opening has a cross-sectional area of no greater than 0.6 mm 2 .
  • the second stem end and the second line end are parallel to one another.
  • Fig. 1 illustrates a gas turbine engine 10 of a type preferably provided for use in subsonic flight, generally comprising in serial flow communication a fan 12 through which ambient air is propelled, a compressor section 14 for pressurizing the air, a combustor 16 in which the compressed air is mixed with fuel and ignited for generating an annular stream of hot combustion gases, and a turbine section 18 for extracting energy from the combustion gases.
  • the gas turbine engine 10 has fuel nozzles 20 or injectors mounted between an annular case 11 of the gas turbine engine 10 and the combustor 16.
  • the case 11 surrounds a cavity E forming an air plenum, hereinafter "engine cavity E", around the combustor 16.
  • the combustor 16 defines a combustion chamber C circumscribed by radially inner and radially outer combustor liners of the combustor 16 inside the engine cavity E.
  • Fig. 2 shows an embodiment of one of the fuel nozzles 20.
  • the illustrated nozzle 20 generally comprises a number of external parts secured together, namely, a flange 30 which is securable to the case 11, a stem 40 adapted to be disposed inside the engine cavity E and extending from the flange 30, and a tip 50 inside the engine cavity E located at the end of the stem 40.
  • the flange 30 is typically bolted to an exterior of the case 11.
  • the stem 40 is configured to structurally support the tip 50 on the flange 30.
  • a portion of the nozzle 20, which may include a portion of the flange 30 and/or a portion of the stem 40, extends from outside the case 11 to inside thereof via an opening defined in the case 11.
  • the tip 50 of the nozzle 20 is positioned so as to extend through a corresponding opening defined in a dome wall portion of the combustor 16, and thus extends from outside the combustion chamber C to inside the combustion chamber C.
  • the tip 50 may be monolithic or, as will be described further below, may comprise a plurality of components 50', 50" suitably assembled. In some embodiments, only one of such components 50', 50" extends through the opening of the combustor 16.
  • a first side 30a of the flange 30 generally faces away from the combustor 16, whereas a second side 30b of the flange 30 generally faces the stem 40 and the combustor 16.
  • a first side 40a of the stem 40 generally faces the flange 30, whereas a second side 40b of the stem 40 generally faces the tip 50.
  • a first side 50a of the tip 50 generally faces the stem 40, whereas a second side 50b of the tip 50 generally faces the combustor 16.
  • fuel is supplied to at least one fuel passage 32, 32' of the flange 30 (or flange passage 32, 32') of the illustrated nozzle 20, in this case from a manifold (not shown) of the engine 10 in fluid communication with a plurality of the fuel nozzles 20 of the engine 10.
  • the at least one fuel passage 32, 32' is defined by the flange 30 so as to suitably condition the flow of fuel downstream of the manifold.
  • the fuel exits the fuel nozzle 20 at the tip 50 via at least one fuel passage 52, 52' thereof (or tip passage 52, 52'), from which it is injected into the combustor 16 and ignited to generate heat.
  • the at least one fuel passage 52, 52' is defined by the tip 50 as to suitably condition the flow of fuel as it flows therein and/or exits therefrom, for example to incorporate air with the fuel so as to generate a spray.
  • the fuel nozzle 20 is configured to provide suitable fluid connection(s) between the fuel passage(s) 32, 32' of the flange 30 and the fuel passage(s) 52, 52' of the tip 50.
  • the fuel nozzle 20 comprises at least one fuel line 60, 60' extending lengthwise, at least partially, inside the stem 40.
  • Each one of the at least one fuel line 60, 60' has two opposite ends, namely a first end 60a, 60'a in fluid communication with a corresponding one of the at least one fuel passages 32, 32' of the flange 30, and a second end 60b, 60'b in fluid communication with a corresponding one of the fuel passages 52, 52' of the tip 50.
  • the first end(s) 60a, 60'a and/or the second end(s) 60b, 60'b may extend outside the stem 40.
  • the fuel nozzle 20 may be referred to as a "simplex" nozzle if it includes a sole fuel line 60, or as a “duplex” nozzle if it includes a pair of fuel lines 60, 60'. Fuel nozzles 20 having more than two fuel lines, and a corresponding number of fuel passages 32, 52, are contemplated.
  • the flange 30 can define one or more flange cavities 34, 36, for example one such cavity 34 located on the second side 30b of the flange 30 for receiving the stem 40, and at least one other such cavity 36 located on the first side 30a of the flange 30 in fluid communication with the at least one fuel passage 32, 32'.
  • the tip 50 can define one or more tip cavities 54, 56, 56', for example one such cavity 54 located on the first side 50a of the tip 50 for receiving the stem 40, and at least one other such cavity 56, 56' located on the second side 50b of the tip 50 in fluid communication with the at least one fuel passage 52, 52'.
  • the stem 40 has a hollow stem body 42 (hereinafter “body”) that in this case is monolithic, and extends peripherally so as to circumscribe a stem chamber 44 inside which the at least one fuel line 60, 60' extends, while providing structure to the stem 40.
  • the at least one fuel line 60, 60' is spaced from the inner wall of the hollow stem body 42 by an annular insulating gap.
  • the stem 40 provides thermal insulation to the at least one fuel line 60, 60'.
  • the stem 40 serves a dual function as it is both a support for the tip 50 and a heat shield for the at least one fuel line 60, 60'.
  • the body 42 is elongated, and extends lengthwise from a first end 42a of the stem 40, also referred to as a proximal end 42a (i.e., the end that is the closest to the flange 30) to a second end 42b (i.e., the end that is the furthest from the flange 30), also referred to as a distal end 42b.
  • the stem body 42 extends proximate to the flange 30 along a first stem axis, such that it is matingly connected to the flange 30 along the first stem axis.
  • the first stem end 42a is matingly received by the flange cavity 34 defined on the second side 30b of the flange 30.
  • the flange 30 may be said to seal the stem chamber 44 from the engine cavity E.
  • the stem body 42 extends proximate to the tip 50 along a second stem axis, such that it is matingly connected to the tip 50 along the second stem axis.
  • the second stem end 42b is matingly received by the tip cavity 54 defined on the first side 50a of the tip 50.
  • the tip 50 may be said to seal the stem chamber 44 from the combustion chamber C and from the engine cavity E.
  • the stem body 42 may be said to follow a certain path as it extends lengthwise.
  • first stem axis and the second stem axis are collinear, and thus correspond to a same axis A.
  • the stem body 42 fully extends along the axis A, and thus follows a linear path. In other embodiments, at least a portion of the stem body 42 may follow a non linear path. In some such embodiments, the first stem axis and the second stem axis may be at an angle relative to one another.
  • the stem body 42 is hollow, and may thus be said to include a peripheral wall having an outer surface 42c (i.e., a surface exposed at least in part to the engine cavity E) and an inner surface 42d (i.e., a surface circumscribing the stem chamber 44).
  • the stem body 42 may be cylindrical in shape, and thus may extend axially and circumferentially relative to the axis A, with the outer surface 42c and the inner surface 42d being spaced by a thickness T relative to the axis A, i.e., in this case a radial thickness, that is the same at the first stem end 42a, at the second stem end 42b, and at either axial position therebetween.
  • the stem body 42 may have an outer diameter and an inner diameter (shown at D) that are constant throughout its length. Other configurations are contemplated for the peripheral wall.
  • the stem 40 and the at least one fuel line 60, 60' are sized and arranged relative to one another so as to provide suitable insulation to the at least one fuel line 60, 60' from the high temperatures in effect in the vicinity of the fuel nozzle 20 as the engine 10 operates.
  • the temperature inside the engine cavity E around the combustor can attain 1000 F, or approximately 537.8 C, whereas it may be desirable to maintain the stem chamber 44 at a temperature of about 600 F, or approximately 315.5 C, to minimize adverse heating of the fuel as it flows inside the at least one fuel line 60, 60'.
  • the inner diameter D of the of the peripheral wall of the stem body 42 is between 7 and 15 times an outer diameter d of the at least one fuel line 60, 60'.
  • the inner diameter D may be of between about 0.4 inch and 0.6 inch, for example 0.5 inch, i.e., between about 10.2 mm and 15.2 mm, for example 12.7 mm.
  • the outer diameter d may be of between about 0.030 inch and 0.090 inch, for example 0.060 inch, i.e., between about 0.76 mm and 2.30 mm, for example 1.52 mm.
  • a portion of the volume circumscribed by the outer surface 42c of the stem body 42 that is occupied by air may be maximised while maintaining the requisite structural integrity of the stem 40 as it holds the tip 50 relative to the flange 30.
  • the thickness T of the peripheral wall of the stem body 42 may be much smaller than the inner diameter D.
  • the thickness T may be of between about 0.035 inch and 0.060 inch, for example 0.050 inch, i.e., between about 0.89 mm and about 1.52 mm, for example 1.27 mm. In embodiments, the thickness T is at least at a location that is spaced away from the flange 30 and from the tip 50.
  • the peripheral wall may have multiple thicknesses at respective lengthwise locations.
  • a thickness of the at least one fuel line 60, 60' may be of between about 0.010 inch and 0.025 inch, for example 0.015 inch, i.e., between about 0.254 mm and 0.635 mm, for example 0.381 mm.
  • An inner diameter of the at least one fuel line 60, 60' may be of between about 0.10 inch and 0.25 inch, i.e., between about 2.5 mm and 6.4 mm.
  • the stem 40 may have an opening 46 defined in the peripheral wall at a location where the outer surface 42c is exposed to the engine cavity E, with the opening 46 extending through the peripheral wall from the inner surface 42d to the outer surface 42c.
  • the opening 46 is thus in fluid communication between the stem chamber 44 and the engine cavity E, and more specifically a portion of the engine cavity E that is outside the combustor 16.
  • the pressure inside the stem chamber 44 may tend to equilibrate with that of the engine cavity E.
  • the opening 46 is sized so as to be small relative to the stem chamber 44 so as to prevent ingress of hot air into the stem chamber 44.
  • the opening 46 may have a cross-sectional area that is of less than about 0.15 % of an area of the outer surface 42c that is exposed to the engine cavity E. In embodiments, the opening 46 has a cross-sectional area that is no greater than about 0.0009 square inches, i.e., no greater than about 0.6 mm 2 . In embodiments, the opening 46 is cylindrical in shape. In some such embodiments, the opening 46 may have a diameter of between about 0.015 inch and 0.025 inch, i.e., between about 0.38 mm and 0.63 mm.
  • the opening 46 may be located closer to the flange 30 than to the tip 50, such that it is spaced away from the heat source (i.e., the combustor 16) and thus less susceptible to let heat enter the stem chamber 44.
  • the opening 46 is a sole opening defined in the peripheral wall. In embodiments, more than one opening 46 is provided in the peripheral wall.
  • Components of the fuel nozzle 20 interfacing one another may be fixedly joined, i.e., permanently joined or in a manner not intended to be disjoined, by various suitable means.
  • the first stem end 42a and the second stem end 42b may be respectively fixedly joined to the flange 30 and to the tip 50 by brazing, welding or soldering.
  • the first line end(s) 60a, 60'a and the second line end(s) 60b, 60'b may be respectively fixedly joined to the flange 30 and to the tip 50 by brazing, welding or soldering.
  • the fuel nozzle 20 may be arranged such that brazing can be used to fixedly join multiple components of the fuel nozzle 20 in one heating operation or, stated otherwise, so that multiple joints of the fuel nozzle 20 may be brazed at once.
  • the opening 46 may serve as a vent during a heat treatment cycle, for example a brazing cycle, so that pressures inside and outside the stem chamber 44 may equilibrate, and/or for gasses generated or used during the heat treatment cycle to evacuate from the stem chamber 44.
  • Fitment of any two components of the fuel nozzle 20 may refer to the secure, yet non permanent assembly of such two components, in some cases with a brazing media (e.g., paste, powder, or preform material) disposed at the interface therebetween.
  • a brazing media e.g., paste, powder, or preform material
  • first stem end 42a may be fitted to a complementary shape of the flange 30, for example the flange cavity 34
  • first line end(s) 60a, 60'a may be fitted to complementary shape(s) of the flange 30, for example distal portion(s) of the fuel passages 32, 32'
  • the second stem end 42b may be fitted to a complementary shape of the tip 50, for example the tip cavity 54
  • the second line end(s) 60b, 60'b may be fitted to complementary shape(s) of the tip 50, for example proximal portion(s) of the fuel passages 52, 52'.
  • the outer surface 42c of the stem body 42 interfaces a radially inner surface of the flange 30 at the first stem end 42a, and interfaces a radially inner surface of the tip 50 at the second stem end 42b.
  • the first and second stem ends 42a, 42b are respectively recessed in, or matingly received by, the flange 30 and the tip 50, such that end portions of the stem chamber 44 may be said to be located inside the flange 30 and inside the tip 50.
  • the stem chamber 44 may extend from inside the flange 30 to inside the tip 50
  • the inner surface 42d of the stem body 42 may interface a radially outer surface of the flange 30 and/or a radially outer surface of the tip 50.
  • the fuel nozzle 20 may be arranged so as to facilitate the simultaneous fitment of the stem 40 and of the at least one fuel line 60, 60' to the flange 30 and/or to the tip 50.
  • the first stem end 42a and the first line end(s) 60a, 60'a may extend parallel to one another, and/or the second stem end 42b and the second line end(s) 60b, 60'b may extend parallel to one another.
  • the tip 50 being fitted onto the stem 40 and onto the at least one fuel line 60, 60'
  • the second stem end 42b and the second line end(s) 60b, 60'b may extend parallel to one another, and/or the first stem end 42a and the first line end(s) 60a, 60'a may extend parallel to one another.
  • the at least one fuel line 60, 60' is cylindrical in shape.
  • the stem 40 and the at least one fuel line 60, 60' are all cylindrical in shape, and extend parallel to one another upon the nozzle 20 being assembled.
  • the flange 30, the stem 40, the tip 50 and/or the at least one fuel line 60, 60' are constructed of material(s) that are suitable for the joining means employed to assemble the nozzle 20.
  • material(s) are metallic materials having a melting temperature that is higher than that of the brazing media.
  • the material(s) have a melting temperature that is of at least 2,200 F (1,206 C).
  • the material(s) of which the stem 40 and/or the at least one fuel line 60, 60' may have particularly desirable properties in accordance with the dual function of the stem 40, for example high rigidity and low thermal conductivity.
  • the stem 40 and/or the at least one fuel line 60, 60' are obtained from standardized structures requiring minimal machining steps before being assembled so as to form the nozzle 20.
  • the stem 40 and/or the at least one fuel line 60, 60' can be made of tubing, in some cases having nominal dimensions that are readily available off-the-shelf.
  • a sole machining step to which the stem 40 and/or the at least one fuel line 60, 60' is/are submitted is lengthwise cutting.
  • the stem body 42 can be provided in the form of an outer tube and the at least one fuel line 60, 60' can be provided in the form of internal tube(s) inside the outer tube, thereby forming a nested tube arrangement.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fuel-Injection Apparatus (AREA)

Claims (12)

  1. Une buse de carburant (20) pour un moteur à turbine (10), comprenant :
    une bride (30) définissant au moins un passage de bride (32, 32') ;
    un embout (50) espacé de la bride (30), l'embout (50) définissant au moins un passage d'embout (52,52') ;
    une tige (40) fournie sous la forme d'un tube droit ayant une première extrémité de tige (42a) fixée de manière permanente à la bride (30) et une seconde extrémité de tige (42b) fixée de manière permanente à l'embout (50), la tige (40) ayant une paroi périphérique se prolongeant longitudinalement le long d'un trajet linéaire entre la première extrémité de tige (42a) et la seconde extrémité de tige (42b) et périphériquement autour d'une chambre de tige (44), la seconde extrémité de tige (42b) étant reçue dans une cavité (54) définie dans l'embout (50), l'embout (50) scellant la chambre de tige (44) à la seconde extrémité de tige (42b) ; et
    au moins une conduite de carburant (60, 60') s'étendant au moins partiellement à l'intérieur de la chambre de tige (44) et ayant une première extrémité de conduite (60a, 60'a) reliée fluidiquement au moins à un passage de bride (32, 32') et une seconde extrémité de conduite (60b, 60'b) reliée fluidiquement au moins à un passage de pointe (52, 52'), la ou les conduites de carburant (60, 60') étant de forme cylindrique et espacées d'une surface intérieure (42d) de la paroi périphérique par un espace isolant annulaire,
    caractérisé en ce que :
    la première extrémité de tige (42a) et la seconde extrémité de tige (42b) sont coaxiales ; et
    un diamètre intérieur (D) de la paroi périphérique est compris entre 7 et 15 fois un diamètre extérieur (d) d'au moins une conduite de carburant (60,60').
  2. La buse de carburant (20) conformément à la revendication 1, selon laquelle la première extrémité de tige (42a) et la seconde extrémité de tige (42b) sont respectivement fixées à la bride (30) et à l'embout (50) par brasage, soudage ou soudure.
  3. La buse de carburant conforme à la revendication 1 ou 2, selon laquelle la première extrémité de conduite (60a,60'a) et la seconde extrémité de conduite (60b,60'b) sont respectivement fixées de manière permanente à la bride (30) et à l'embout (50) par brasage, soudage ou soudure.
  4. La buse de carburant (20) conformément à l'une des revendications précédentes, selon laquelle la première extrémité de tige (42a) et la seconde extrémité de tige (42b) sont respectivement reçues de manière ajustée et complémentaire par la bride (30) et l'embout (50), de sorte que la chambre de tige (44) se prolonge de l'intérieur de la bride (30) jusqu'à l'intérieur de l'embout (50).
  5. La buse de carburant (20) conformément à l'une des revendications précédentes, selon laquelle la première extrémité de tige (42a) et la seconde extrémité de tige (42b) sont de forme cylindrique.
  6. La buse de carburant (20) conformément à l'une des revendications précédentes, selon laquelle la tige (40) présente une épaisseur de paroi constante sur toute sa longueur.
  7. La buse de carburant (20) conformément à l'une des revendications précédentes, selon laquelle la paroi périphérique présente une épaisseur comprise entre 0,89 mm et 1,52 mm à un endroit situé à distance de la bride (30) et de l'embout (50).
  8. La buse de carburant (20) conformément à l'une des revendications précédentes, selon laquelle le diamètre interne (D) de la paroi périphérique est compris entre 10,2 mm et 15,2 mm.
  9. La buse de carburant (20) conformément à l'une des revendications précédentes, selon laquelle la tige présente une ouverture (46) définie dans la paroi périphérique à un emplacement intermédiaire entre l'embout (50) et la bride (30), l'ouverture (46) étant en communication fluide entre la chambre de tige (44) et l'extérieur de la buse de carburant (20).
  10. La buse de carburant (20) conformément à la revendication 9, selon laquelle l'ouverture (46) est située plus près de la bride (30) que de l'embout (50).
  11. La buse de carburant (20) conformément à la revendication 9 ou 10, selon laquelle l'ouverture (46) présente une surface de section transversale inférieure à 0,6 mm2.
  12. Un moteur à turbine (10) comprenant :
    un boîtier (11) entourant un plénum d'air (E) ;
    un chambre de combustion (16) entourée par le plénum d'air (E), la chambre de combustion (16) définissant une chambre de combustion (C) ;
    une buse de carburant (20) selon l'une quelconques des revendications précédentes, la buse de carburant (20) étant conçue pour injecter un mélange air-carburant dans la chambre de combustion (C).
EP23197278.7A 2022-09-15 2023-09-13 Buse de carburant Active EP4339515B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US17/932,319 US20240093869A1 (en) 2022-09-15 2022-09-15 Fuel nozzle

Publications (2)

Publication Number Publication Date
EP4339515A1 EP4339515A1 (fr) 2024-03-20
EP4339515B1 true EP4339515B1 (fr) 2025-05-14

Family

ID=88068925

Family Applications (1)

Application Number Title Priority Date Filing Date
EP23197278.7A Active EP4339515B1 (fr) 2022-09-15 2023-09-13 Buse de carburant

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US (1) US20240093869A1 (fr)
EP (1) EP4339515B1 (fr)
CA (1) CA3210482A1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN119042663B (zh) * 2024-09-14 2025-09-23 中国人民解放军国防科技大学 一种喷注超临界煤油的超声速燃烧室地面实验系统

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6076356A (en) * 1996-03-13 2000-06-20 Parker-Hannifin Corporation Internally heatshielded nozzle
JP4323723B2 (ja) * 1998-10-09 2009-09-02 ゼネラル・エレクトリック・カンパニイ ガスタービンエンジン燃焼器の燃料噴射組立体
US20160116168A1 (en) * 2014-10-27 2016-04-28 Solar Turbines Incorporated Robust insulated fuel injector for a gas turbine engine
US10865714B2 (en) * 2018-03-22 2020-12-15 Woodward. Inc. Gas turbine engine fuel injector
US11162682B2 (en) * 2019-10-11 2021-11-02 Solar Turbines Incorporated Fuel injector
JP7320466B2 (ja) * 2020-02-28 2023-08-03 本田技研工業株式会社 ガスタービン用燃料噴射装置

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EP4339515A1 (fr) 2024-03-20
CA3210482A1 (fr) 2024-03-15
US20240093869A1 (en) 2024-03-21

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