US3056261A - Flameholder configuration - Google Patents

Flameholder configuration Download PDF

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Publication number
US3056261A
US3056261A US837543A US83754359A US3056261A US 3056261 A US3056261 A US 3056261A US 837543 A US837543 A US 837543A US 83754359 A US83754359 A US 83754359A US 3056261 A US3056261 A US 3056261A
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US
United States
Prior art keywords
flameholder
ring
configuration
rings
members
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.)
Expired - Lifetime
Application number
US837543A
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English (en)
Inventor
Roy A Krabacher
Everett W Waters
Henry E Kamps
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Priority to US837543A priority Critical patent/US3056261A/en
Priority to CH982360A priority patent/CH389996A/de
Application granted granted Critical
Publication of US3056261A publication Critical patent/US3056261A/en
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F23R3/02—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

Definitions

  • the present invention relates to a flameholder configuration for aircraft jet engine afterburners and more particularly to an improved tiameholder configuration in which thermal and gas load bending stresses are reduced to a minimum.
  • V-gutters which are rigidly supported in the turbine discharge passage of the engine between the structural shell of the engine tailpipe and the tailcone. Since the flame holder is suspended within the tailpipe it is exposed to the engine exhaust gases. The high velocity exhaust gases impinge directly on the V-gutters and supporting members and imposed aerodynamic loading stresses thereon. The wide temperature range of the exhaust gases causes differential expansion and contraction of the V-gutters, thus creating thermal stresses in the ameholder. ln conventional flameholder designs V-gutters and support members have been provided with rigid interconnections and massive cross-sections in order to resist the stresses imposed by the exhaust gases.
  • the tailpipe and tailcone have had to be of massive construction in order to resist the bending moments acting on the flameholder support members.
  • the effective operating life of the flameholder generally varies directly with the mass and weight of its components. This has presented a severe problem in the design of aircraft jet engines since weight is a critical factor of engine design.
  • An object of the present invention is to provide a flameholder configuration which is light and strong and has an increased effective life over heretofore known designs.
  • the above object is realized in the present invention by provision of a flameholder configuration which eliminates or reduces to a minimum the gas load bending stresses and torsional stresses in the flameholder rings and eliminates gas load bending stresses from the supporting members. This is accomplished by interconnection of the ameholder rings, support members and structural members of the engine by pin connections which allow the rings to expand and contract individually and which allow all tensile forces to be transmitted through the shear center of the ring cross-sections.
  • AFIG. 1 is an elevation view partly in section of a portion of -a jet engine in which the present invention is installed;
  • FIG. 2. is an elevation view at an enlarged scale of the flameholder configuration of FIG. 1;
  • IFIG. 3 is a schematic view of the flameholder configuration of the present invention showing the location and disposition of gas loads and tensile forces.
  • the ameholder configuration of the present invention is shown as installed in a jet engine downstream of turbine wheels and 11, and within turbine discharge passage 12 which is defined by the engine tailpipe 13 and the tailcone 14.
  • the ameholder configuration of the present invention is mounted on the tailcone 14 and includes three concentric flameholder rings 15, 15 and 17 interconnected by radial links 18 and 19.
  • Another link 21 connects the flameholder assembly to a bracket ZG which is secured to the tailcone.
  • each of the flameholder rings includes an upper and lower arm, 222 and 23, joined to a tubular member 24 which for-ms the apex of the V.
  • a clevis connector 25- is secured to the tubular member of ring 16 and extends forwardly and downwardly therefrom.
  • a similar clevis connector 26 is secured to the tubular member of ring 17 and extends forwardly and upwardly therefrom.
  • a generally C-shaped clevis connector 27 is secured to the tubular portion of ring 15 and extends downstream thereof adjacent the upper and lower arms of the ring.
  • Link 18 is secured to connectors 25 and 27 by means of pins 28 and 29.
  • Link 19 is similarly secured to connectors 26 and 27 by pins 31 and 32.
  • a clevis connector 35 is secured to the bracket 2f).
  • Link 21 is connected to connectors 27 and 35 by means of pins 36 and 37.
  • the individual flameholder rings are pivotally connected to each other and to the structural member (tailcone 11i) they are each free to expand and contract individually. lf one of the llameliolder rings expands or contracts at a different rate, or to a different degree than another, it merely moves relative to the other ring. No stresses are transmitted from one to another by uneven expansion or contraction. Accordingly, thermal stresses due to differential expansion and contraction are avoided in the present flameholder configuration.
  • An additional feature ⁇ of the present flameholder contiguration is the use of a pin-clevis connection between link 21 and tailcone 114. By means of this connection, the forces due to the aerodynamic drag loads on the flameholders ⁇ are transmitted to the tailcone in pure tension, thus eliminating any bending moment due to such loads.
  • link 21 may be secured to the tailcone, the tailpipe, or to a transverse strut as long as the line of action of force T3 passes through the center of shear of lameholder ring 1S.
  • the center of shear of the V-gutter configuration shown closely approaches the center of the tubular member. Accordingly, for all practical purposes the condition of no torsional stress can be achieved by having the lines of action of the tensile forces pass through the center of the cross-section of the tubular member.
  • An afterburner ilameholder assembly for use in a jet exhaust pipe, said assembly comprising: a plurality of annular gutter members including iirst, second, and third ring members, said ring members being coaxial and of different diameters with said third ring member positioned intermediate of said first and second members; ⁇ and support means for said assembly including a first plurality of linking members pivotally interconnecting and locating said rst and second ring members relative to said third ring member, and a second plurality of linking members pivotally connecting and locating said ⁇ assembly relative to the pipe, wherein the lines of action ⁇ of the tensile forces developed in said pluralities ⁇ of linking mem-bers by impingement of the exhaust stream on said gutter members pass through the shear centers of said ring members, so that induced bending stresses in said linking members are eliminated and induced torsional stresses in said ring members are minimized.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)
US837543A 1959-09-01 1959-09-01 Flameholder configuration Expired - Lifetime US3056261A (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
US837543A US3056261A (en) 1959-09-01 1959-09-01 Flameholder configuration
CH982360A CH389996A (de) 1959-09-01 1960-08-31 Flammenhalteranordnung

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US837543A US3056261A (en) 1959-09-01 1959-09-01 Flameholder configuration

Publications (1)

Publication Number Publication Date
US3056261A true US3056261A (en) 1962-10-02

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Family Applications (1)

Application Number Title Priority Date Filing Date
US837543A Expired - Lifetime US3056261A (en) 1959-09-01 1959-09-01 Flameholder configuration

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US (1) US3056261A (de)
CH (1) CH389996A (de)

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3496676A (en) * 1968-10-29 1970-02-24 Williamsburg Steel Products Co Door seal construction
US3540216A (en) * 1967-01-23 1970-11-17 Snecma Two-flow gas turbine jet engine
US3646763A (en) * 1970-05-25 1972-03-07 Gen Electric Gas turbine engine with improved afterburner
US3670501A (en) * 1970-06-29 1972-06-20 Gen Electric Gas turbine engine with improved afterburner
US3768251A (en) * 1971-01-19 1973-10-30 Etude Construction Moteurs D A Fixing of fuel injection manifolds into combustion chambers
FR2330867A1 (fr) * 1975-11-04 1977-06-03 Gen Electric Stabilisateur de flamme amovible
US4490973A (en) * 1983-04-12 1985-01-01 The United States Of America As Represented By The Secretary Of The Air Force Flameholder with integrated air mixer
US4594851A (en) * 1983-12-16 1986-06-17 The United States Of America As Represented By The Secretary Of The Air Force Flameholder with removable flameholder attachments
US4802337A (en) * 1986-02-27 1989-02-07 Societe Nationale D-Etude Et De Construction De Moteurs D-Aviation (Snecma) Flameholder for a turbojet engine afterburner
US4901527A (en) * 1988-02-18 1990-02-20 General Electric Company Low turbulence flame holder mount
US5022805A (en) * 1989-02-16 1991-06-11 Rolls-Royce Incorporated Cantilever mounting system for structural members having dissimilar coefficients of thermal expansion
US5367873A (en) * 1991-06-24 1994-11-29 United Technologies Corporation One-piece flameholder
US20120205914A1 (en) * 2009-09-30 2012-08-16 Marcus Reich Wind energy converter

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2696709A (en) * 1950-09-27 1954-12-14 Rolls Royce Combustion system of internalcombustion engines
US2714287A (en) * 1950-01-03 1955-08-02 Westinghouse Electric Corp Flameholder device for turbojet afterburner
US2726511A (en) * 1950-05-18 1955-12-13 Solar Aircraft Co Afterburners
US2793495A (en) * 1951-05-01 1957-05-28 Gen Motors Corp Jet propulsion combustion apparatus with expansibly mounted fuel manifold
US2874536A (en) * 1954-03-18 1959-02-24 Gen Electric Cooling means for tailpipe
US2944399A (en) * 1956-05-31 1960-07-12 Gen Electric Afterburner combustion means

Patent Citations (6)

* 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
US2726511A (en) * 1950-05-18 1955-12-13 Solar Aircraft Co Afterburners
US2696709A (en) * 1950-09-27 1954-12-14 Rolls Royce Combustion system of internalcombustion engines
US2793495A (en) * 1951-05-01 1957-05-28 Gen Motors Corp Jet propulsion combustion apparatus with expansibly mounted fuel manifold
US2874536A (en) * 1954-03-18 1959-02-24 Gen Electric Cooling means for tailpipe
US2944399A (en) * 1956-05-31 1960-07-12 Gen Electric Afterburner combustion means

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3540216A (en) * 1967-01-23 1970-11-17 Snecma Two-flow gas turbine jet engine
US3496676A (en) * 1968-10-29 1970-02-24 Williamsburg Steel Products Co Door seal construction
US3646763A (en) * 1970-05-25 1972-03-07 Gen Electric Gas turbine engine with improved afterburner
US3670501A (en) * 1970-06-29 1972-06-20 Gen Electric Gas turbine engine with improved afterburner
US3768251A (en) * 1971-01-19 1973-10-30 Etude Construction Moteurs D A Fixing of fuel injection manifolds into combustion chambers
FR2330867A1 (fr) * 1975-11-04 1977-06-03 Gen Electric Stabilisateur de flamme amovible
US4490973A (en) * 1983-04-12 1985-01-01 The United States Of America As Represented By The Secretary Of The Air Force Flameholder with integrated air mixer
US4594851A (en) * 1983-12-16 1986-06-17 The United States Of America As Represented By The Secretary Of The Air Force Flameholder with removable flameholder attachments
US4802337A (en) * 1986-02-27 1989-02-07 Societe Nationale D-Etude Et De Construction De Moteurs D-Aviation (Snecma) Flameholder for a turbojet engine afterburner
US4901527A (en) * 1988-02-18 1990-02-20 General Electric Company Low turbulence flame holder mount
US5022805A (en) * 1989-02-16 1991-06-11 Rolls-Royce Incorporated Cantilever mounting system for structural members having dissimilar coefficients of thermal expansion
US5367873A (en) * 1991-06-24 1994-11-29 United Technologies Corporation One-piece flameholder
US20120205914A1 (en) * 2009-09-30 2012-08-16 Marcus Reich Wind energy converter

Also Published As

Publication number Publication date
CH389996A (de) 1965-03-31

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