US3646763A - Gas turbine engine with improved afterburner - Google Patents

Gas turbine engine with improved afterburner Download PDF

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Publication number
US3646763A
US3646763A US40298A US3646763DA US3646763A US 3646763 A US3646763 A US 3646763A US 40298 A US40298 A US 40298A US 3646763D A US3646763D A US 3646763DA US 3646763 A US3646763 A US 3646763A
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Prior art keywords
gutters
links
afterburner
turbine engine
gas turbine
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Expired - Lifetime
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US40298A
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English (en)
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John K Arand
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General Electric Co
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General Electric Co
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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
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
    • F23R3/20—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants incorporating fuel injection means

Definitions

  • GAS TURBINE ENGINE WITH IMPROVED AFTERBURNER [72] Inventor: John K. Arand, Palos Verdes Peninsula,
  • ABSTRACT An afterbumer for a gas turbine engine comprising fuel injectors and concentric, annular, V-shaped gutters which function as flameholders. Links are pivotally mounted at their opposite ends to the gutters and to beams. The beams are pivoted on the outer casing of the afterburner and align the pivot axes of the links and the bisectors of the gutters with the direction of hot gas flow toward the gutters in the hot condition of the afterbumer to prevent twisting of the gutters when their material strength is weakest.
  • the present invention relates to improvements in gas turbine engines having afterbumers for augmenting the energy level of a hot gas stream to be discharged from a propulsion nozzle.
  • afterburners fuel is injected into a hot gas stream to augment its energy level.
  • Flameholders are mounted immediately downstream of the injectors to establish a stable framefront or localized combustion zone for the augmenting fuel.
  • V-shaped sheet metal gutters have been found to be quite effective as flameholders. Such flameholders must operate in an area of extremely high temperature at which the strength of the gutter material is quite low. Because of the relatively thin metal sections required by weight limitations and for other reasons, flameholder gutters have been subject to bending and twisting loads which result in distortion of the gutters in relatively short periods of operation.
  • the primary object of the invention is to prevent bending, twisting and other deformation of flameholder gutters in a simple, effective manner to thereby significantly increase their service life.
  • a mounting system which, when the afterburner is in operation in its hot condition, aligns the bisector of the V-shaped gutter and the pivot axes of mounting links with the direction of flow of the hot gas stream toward the gutter.
  • the links are mounted on beams which are pivoted on the casing of the afterburner section of the engine and have pivoted links connecting their inner ends to a central casing or plug.
  • FIG. 1 is a schematic showing of a gas turbine engine incorporating an afterburner for supersonic propulsion
  • FIG. 2 is a partial longitudinal section showing the afterburner in greater detail in its hot position
  • FIG. 3 is a section taken on line IIlIIl in FIG. 2;
  • F IG. 4 is a section taken on line IVIV in FIG. 2;
  • FIG. 5 is a section similar to FIG. 2 showing the afterburner flameholder in a cold position.
  • FIG. 1 schematically illustrates a gas turbine engine of the type employed for supersonic flight.
  • Air enters an inlet comprising a spike I0 and is then compressed in an axial flow compress'or 12. This compressed air supports combustion of fuel in a combustor 14 to generate a hot gas stream.
  • the hot gas stream drives a turbine 16 which in turn, through a shaft 18, powers the rotor of the compressor 12.
  • the energy level of the hot gas stream is then augmented by the combustion of further fuel in an afterburner or augmenter 20.
  • the augmented gas stream is then discharged from a variable area, convergentdivergent nozzle 22 to provide the necessary thrust for supersonic flight.
  • the hot gas stream may or may not be augmented in the afterburner and the nozzle may be adjusted to other than the illustrated convergent-divergent configuration.
  • the hot gas stream has an annular flowpath as it enters the afterburner.
  • This flowpath is defined by an engine casing 24 and a central plug 26 which is supported on appropriate frame structure (not shown).
  • the afterburner includes fuel injectors 30 (see also FIG. 4) and flameholders in the form of annular V-shaped gutters 32.
  • the injectors may comprise tube bundles which are mounted in angularly spaced relation on the casing 24. Openings in the tubes spray fuel into the hot gas stream and a stabilized flamefront or combustion zone is maintained by the gutters 32. This type of an afterburner combustion mechanism is known per se.
  • the gutters 32 are preferably in the form of sheet metal fabrications having mounting lug openings 36 in their troughs or apices (FIG. 3).
  • Mounting lugs 38 extend through the openings 36 and have wings 40 curved to match the troughs of the gutters. These wings are secured to the gutters, as by brazing.
  • Links 42 are connected on opposite sides of each lug 38 by pins 44. The opposite ends of each pair of links 42 are connected by pins 46 to beams 48 angularly spaced around the casing 24. As can be seen from FIG. 4, there is a linkage con nection between each beam and each gutter.
  • Each of the beams 48 is pivotally mounted, at its outer end, on the casing 24 by a pin 50 and a lug 52 secured to the casing.
  • a link 54 is connected to each beam 48, adjacent its inner end, by a pin 56.
  • Each link 54 is angled in an upstream direction toward the plug 26 and is pivotally connected thereto by a pin 58 extending through a lug 60.
  • the gutters 32 operate in an extremely hot environment resulting in greatly reduced load carrying capacity of the gutter material as compared with more normal lower temperature environments.
  • the described mounting system is particularly adapted to minimize stresses on the gutters when the hot gas stream is at a maximum temperature and metal strength is at a minimum.
  • the gutters and the overall support system therefor are dimensioned (as could be done by a person skilled in the art) so that at the hottest normal operating condition the bisector of the gutter angle, line x in FIG. 2, is aligned with the axes of the associated linkage pins 44 and 46 and also aligned with the direction of hot gas stream flow toward the gutter. This means that there are no twisting forces on the gutters and the stresses thereon are reduced to the simple, minimum level imposed by the hot gas stream in the direction of flow.
  • FIG. 5 illustrates a cold" position of the gutter mounting assembly within the hot position shown by broken lines for comparison. From this Figure it will be seen that when the described alignment of the bisector x is not maintained there is a moment arm either about the gutter relative to the axis of pin 46, or both. In any case a twisting of the gutter occurs which imposes higher stresses on the gutter beyond the minimum stress condition, described in connection with FIG. 2. However, higher stresses can be tolerated at such a cold" condition due to the increased strength capabilities of the gutter material at reduced temperatures, albeit such reduced temperatures may be in excess of l,200 F.
  • a gas turbine engine comprising: means for generating a hot gas stream, a propulsive nozzle from which the hot gas stream is discharged, and
  • an afterbumer for increasing the energy level of the hot gas stream immediately prior to its discharge from the propulsive nozzle, said afterbumer comprising,
  • flameholder means in the form of a plurality of concentric
  • annular, V-shaped gutters each having its apex in an upstream direction toward said fuel injectors, each gutter having a bisector which extends from its apex intermediate its sides,
  • the mounting means comprise a plurality of beams pivotally mounted on said outer casing and angularly spaced therearound.
  • the afterbumer additionally includes an inner plug and the mounting means further includes links respectively angled from the inner end portions of said beams upstream toward said plug,
  • said beam links being pivotally connected at their opposite ends respectively to said beans and to said plug.
  • lugs are secured to the gutters, extend in an upstream direction and are aligned with the bisectors of said gutters and the downstream ends of the links are pivotally connected to said lugs,

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Combustion Of Fluid Fuel (AREA)
  • Control Of Turbines (AREA)
US40298A 1970-05-25 1970-05-25 Gas turbine engine with improved afterburner Expired - Lifetime US3646763A (en)

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US4029870A 1970-05-25 1970-05-25

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US3646763A true US3646763A (en) 1972-03-07

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US40298A Expired - Lifetime US3646763A (en) 1970-05-25 1970-05-25 Gas turbine engine with improved afterburner

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US (1) US3646763A (enrdf_load_stackoverflow)
BE (1) BE763178A (enrdf_load_stackoverflow)
CA (1) CA927616A (enrdf_load_stackoverflow)
DE (1) DE2108690A1 (enrdf_load_stackoverflow)
FR (1) FR2090250B1 (enrdf_load_stackoverflow)
GB (1) GB1335746A (enrdf_load_stackoverflow)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3768251A (en) * 1971-01-19 1973-10-30 Etude Construction Moteurs D A Fixing of fuel injection manifolds into combustion chambers
US4815283A (en) * 1987-06-25 1989-03-28 The United States Of America As Represented By The Secretary Of The Air Force Afterburner flameholder construction
US5335490A (en) * 1992-01-02 1994-08-09 General Electric Company Thrust augmentor heat shield
US6351941B1 (en) * 2000-02-29 2002-03-05 General Electric Company Methods and apparatus for reducing thermal stresses in an augmentor
US20070245743A1 (en) * 2006-04-20 2007-10-25 United Technologies Corporation Augmentor variable vane flame stabilization

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2551500B1 (fr) * 1983-09-07 1985-11-08 Snecma Anneau-bruleur pour postcombustion de moteur a reaction
FR2586792B1 (fr) * 1985-09-03 1989-06-16 Snecma Dispositif de liaison entre un anneau bruleur ou accroche-flammes en materiau composite et un canal de chambre de post-combustion d'un turboreacteur
US5103638A (en) * 1990-01-29 1992-04-14 Rolls-Royce Inc. Mounting arrangement

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2714287A (en) * 1950-01-03 1955-08-02 Westinghouse Electric Corp Flameholder device for turbojet afterburner
GB821286A (en) * 1956-06-05 1959-10-07 Rolls Royce Improvements in or relating to reheat combustion equipment of jet-propulsion engines
US3056261A (en) * 1959-09-01 1962-10-02 Gen Electric Flameholder configuration
US3102392A (en) * 1959-04-21 1963-09-03 Snecma Combustion equipment for jet propulsion units
GB944202A (en) * 1961-07-11 1963-12-11 Rolls Royce Improvements in or relating to combustion equipment and ignition devices therefor

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1245920A (fr) * 1960-01-19 1960-11-10 Le Ministre De La Defense Nati Collecteur de distribution de combustible isolé
FR1265727A (fr) * 1960-08-23 1961-06-30 Gen Electric Structure de tubes à flammes pour brûleurs de post-combustion de turbo-réacteurs
FR1406603A (fr) * 1964-06-09 1965-07-23 Snecma Dispositif de brûleur et son montage dans une chambre de combustion

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2714287A (en) * 1950-01-03 1955-08-02 Westinghouse Electric Corp Flameholder device for turbojet afterburner
GB821286A (en) * 1956-06-05 1959-10-07 Rolls Royce Improvements in or relating to reheat combustion equipment of jet-propulsion engines
US3102392A (en) * 1959-04-21 1963-09-03 Snecma Combustion equipment for jet propulsion units
US3056261A (en) * 1959-09-01 1962-10-02 Gen Electric Flameholder configuration
GB944202A (en) * 1961-07-11 1963-12-11 Rolls Royce Improvements in or relating to combustion equipment and ignition devices therefor

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3768251A (en) * 1971-01-19 1973-10-30 Etude Construction Moteurs D A Fixing of fuel injection manifolds into combustion chambers
US4815283A (en) * 1987-06-25 1989-03-28 The United States Of America As Represented By The Secretary Of The Air Force Afterburner flameholder construction
US5335490A (en) * 1992-01-02 1994-08-09 General Electric Company Thrust augmentor heat shield
US6351941B1 (en) * 2000-02-29 2002-03-05 General Electric Company Methods and apparatus for reducing thermal stresses in an augmentor
US20070245743A1 (en) * 2006-04-20 2007-10-25 United Technologies Corporation Augmentor variable vane flame stabilization
US7712315B2 (en) * 2006-04-20 2010-05-11 United Technologies Corporation Augmentor variable vane flame stabilization

Also Published As

Publication number Publication date
BE763178A (fr) 1971-07-16
FR2090250A1 (enrdf_load_stackoverflow) 1972-01-14
FR2090250B1 (enrdf_load_stackoverflow) 1975-01-17
CA927616A (en) 1973-06-05
DE2108690A1 (de) 1972-08-10
GB1335746A (en) 1973-10-31

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