US3913319A - Low drag flameholder - Google Patents

Low drag flameholder Download PDF

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Publication number
US3913319A
US3913319A US222853A US22285372A US3913319A US 3913319 A US3913319 A US 3913319A US 222853 A US222853 A US 222853A US 22285372 A US22285372 A US 22285372A US 3913319 A US3913319 A US 3913319A
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United States
Prior art keywords
flameholder
bodies
gap
vertex
mixture
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Expired - Lifetime
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US222853A
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Patrick H Hall
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US Department of Navy
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US Department of Navy
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Priority to US222853A priority Critical patent/US3913319A/en
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    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/16Continuous 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
    • F23R3/18Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
    • F23R3/20Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants incorporating fuel injection means

Definitions

  • ABSTRACT A flameholder formed of two streamlined bodies separated by a gap forming spacer.
  • the combustible fuel fed upstream of the flameholder fills the gap where it is ignited with the gap acting as a piloting zone continuously igniting the flowing mixture which is replenished.
  • This invention pertains to flameholders for holding a piloting flame in a combustor.
  • recirculation zones for flameholding have been created by the use of a bluff body.
  • the bluff body has a separation and recirculation zone in its near wake.
  • the bluff body is a high drag device and the size of the unconfined recirculation zone is dependent on local flow conditions and is inherently unsteady due to the nature of the vortex shedding.
  • the primary advantage of the invention is that the flameholding zone is provided by a shape that is low in drag.
  • the drag is low because the gap is always filled, hence the mixture flow sees essentially an aerodynamically smooth configuration. Since the recirculation zone is constrained to be of a constant size, this flameholder will operate over a wide range of flow conditions.
  • An object of this invention is to create a stable recirculation zone to hold a piloting flame in a ramjet combustor.
  • the invention is a fiameholder of a generally spheroidal configuration formed of two streamlined bodies separated by a gap-forming spacer.
  • the combustible fuel which comes from upstream of the fiameholder fills the gap where it is ignited.
  • the gap acts as a piloting zone by continuously igniting the flowing fuel mixture which is replenished by a scavenging process.
  • FIGURE shows a side elevational view of the invention.
  • the invention comprises forward and rearward streamlined bodies of revolution 1 and 2, respectively, separated by spacer 3. This results in a generally spheroidal configuration of the invention with a gap between bodies 1 and 2.
  • the flameholder is fastened to a combustor wall by one or more streamlined struts 4.
  • the fuel is introduced into the combustor through injector 6 in a direction opposite to the air flow.
  • the fuel mixes with the air in such a way that a combustible mixture results.
  • This mixture is carried down stream and fills the gap or recirculation zone between bodies 1 and 2 where it is ignited.
  • a scavenging process takes place at the boundary between the flowing mixture and the stagnant gases in the gap thus replenishing the mixture that is burned in the gap.
  • the gap then acts as a piloting zone, continuously igniting the flowing mixture and at the same time being replenished by it.
  • a fiameholder for use in a combustor comprising:
  • first and second streamline paraboloidal shaped bodies each having a vertex and an end surface portion
  • cylindrical spacer having its diameter substantially smaller than the diameter of said end portions and positioned between said first and second bodies with the flat surface ends of said spacer in contact with the end surface of the first and second bodies to form a substantial gap therebetween;
  • a streamline strut attached to one of said bodies for holding said fiameholder in spaced relationship to the wall of a combuster with the longitudinal axis of said flameholder parallel to air flow through the combustor;
  • a fuel conduit extending through said strut and through the axis of at least one of said bodies to terminate at the vertex of said body on the upstream side of the air flow;

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Spray-Type Burners (AREA)
  • Combustion Of Fluid Fuel (AREA)

Abstract

A flameholder formed of two streamlined bodies separated by a gap forming spacer. The combustible fuel fed upstream of the flameholder fills the gap where it is ignited with the gap acting as a piloting zone continuously igniting the flowing mixture which is replenished.

Description

United States Patent [191 Hall [ Oct. 21, 1975 LOW DRAG FLAMEHOLDER [75] Inventor: Patrick H. Hall, China Lake, Calif.
[73] Assignee: The Unites States of America as represented by the Secretary of the Navy, Washington, DC.
22 Filed: Feb. 2, 1972 21 Appl. No.: 222,853
[52] US. Cl 60/39.72 R; 60/3974 R; 431/350 [51] Int. Cl. F02C 7/22 [58] Field of Search 60/3972 R, 39.74 R; 431/350 [56] References Cited UNITED STATES PATENTS 2,625,795 1/1953 Brzozowski 60/3972 R 2,692,480 10/1954 Viaud et al. 60/39.72 R
2,715,813 8/1955 Holmes et al. 60/3974 R 2,955,419 10/1960 Malick 60/3972 R X AlRFLOW 3,300,976 l/1967 Coplin 60/3974 R X 3,328,958 7/1967 Canuel. 60/3972 R 3,455,108 7/1969 Clare et al. 60/3972 R 3,465,525 9/1969 Cowley et al. 60/3972 R X 3,605,407 9/1971 Bryce 60/3972 R 3,701,255 10/1972 Markowski 60/3972 R Primary Examiner-C. J. Husar Assistant Examiner-Robert E. Garrett Attorney, Agent, or Firm-R. S, Sciascia; Roy Miller; Robert F. Beers [57] ABSTRACT A flameholder formed of two streamlined bodies separated by a gap forming spacer. The combustible fuel fed upstream of the flameholder fills the gap where it is ignited with the gap acting as a piloting zone continuously igniting the flowing mixture which is replenished.
1 Claim, 1 Drawing Figure US. Patent Oct.21, 1975 3,913,319
LOW DRAG FLAMEHOLDER BACKGROUND OF THE INVENTION 1. Field of the Invention.
This invention pertains to flameholders for holding a piloting flame in a combustor.
2. Description of the Prior Art.
In the past, recirculation zones for flameholding have been created by the use of a bluff body. The bluff body has a separation and recirculation zone in its near wake. The bluff body is a high drag device and the size of the unconfined recirculation zone is dependent on local flow conditions and is inherently unsteady due to the nature of the vortex shedding.
The primary advantage of the invention is that the flameholding zone is provided by a shape that is low in drag. The drag is low because the gap is always filled, hence the mixture flow sees essentially an aerodynamically smooth configuration. Since the recirculation zone is constrained to be of a constant size, this flameholder will operate over a wide range of flow conditions.
SUMMARY OF THE INVENTION An object of this invention is to create a stable recirculation zone to hold a piloting flame in a ramjet combustor.
The invention is a fiameholder of a generally spheroidal configuration formed of two streamlined bodies separated by a gap-forming spacer. The combustible fuel which comes from upstream of the fiameholder fills the gap where it is ignited. The gap acts as a piloting zone by continuously igniting the flowing fuel mixture which is replenished by a scavenging process.
BRIEF DESCRIPTION OF THE DRAWING The FIGURE shows a side elevational view of the invention.
DESCRIPTION OF THE PREFERRED EMBODIMENT The invention comprises forward and rearward streamlined bodies of revolution 1 and 2, respectively, separated by spacer 3. This results in a generally spheroidal configuration of the invention with a gap between bodies 1 and 2. The flameholder is fastened to a combustor wall by one or more streamlined struts 4.
Fuel flows through the strut via conduit 7, indicated by dashed lines, in the direction of the arrows. The fuel is introduced into the combustor through injector 6 in a direction opposite to the air flow.
The fuel mixes with the air in such a way that a combustible mixture results. This mixture is carried down stream and fills the gap or recirculation zone between bodies 1 and 2 where it is ignited. As the fuel-air mixture flows over the gap a scavenging process takes place at the boundary between the flowing mixture and the stagnant gases in the gap thus replenishing the mixture that is burned in the gap. The gap then acts as a piloting zone, continuously igniting the flowing mixture and at the same time being replenished by it.
What is claimed is:
l. A fiameholder for use in a combustor comprising:
first and second streamline paraboloidal shaped bodies each having a vertex and an end surface portion;
cylindrical spacer having its diameter substantially smaller than the diameter of said end portions and positioned between said first and second bodies with the flat surface ends of said spacer in contact with the end surface of the first and second bodies to form a substantial gap therebetween;
. a streamline strut attached to one of said bodies for holding said fiameholder in spaced relationship to the wall of a combuster with the longitudinal axis of said flameholder parallel to air flow through the combustor; and
a fuel conduit extending through said strut and through the axis of at least one of said bodies to terminate at the vertex of said body on the upstream side of the air flow;
whereby flow of fuel through the conduit exits into the air stream at the vertex forming a combustible mixture that is carried over the surface of the upstream body to the gap area to replenish the mixture of gases within the gap establishing a stable recirculation zone at a piloting flame.

Claims (1)

1. A flameholder for use in a combustor comprising: FIRST AND SECOND STREAMLINE PARABOLOIDAL SHAPED BODIES EACH HAVING A VERTEX AND AN END SURFACE PORTION; CYLINDRICAL SPACER HAVING ITS DIAMETER SUBSTANTIALLY SMALLER THAN THE DIAMETER OF SAID END PORTIONS AND POSITIONED BETWEEN SAID FIRST AND SECOND BODIES WITH THE FLAT SURFACE ENDS OF SAID SPACER IN CONTACT WITH THE END SURFACE OF THE FIRST AND SECOND BODIES TO FORM A SUBSTANTIAL GAP THEREBETWEEN; A STREAMLINE STRUT ATTACHED TO ONE OF SAID BODIES FOR HOLDING SAID FLAMEHOLDER IN SPACED RELATIONSHIP TO THE WALL OF A COMBUSTER WITH THE LONGITUDINAL AXIS OF SAID FLAMEHOLDER PARALLEL TO AIR FLOW THROUGH THE COMBUSTOR; AND A FUEL CONDUIT EXTENDING THROUGH SAID STRUT AND THROUGH THE AXIS OF AT LEAST ONE OF SAID BODIES TO TERMINATE AT THE VERTEX OF SAID BODY ON THE UPSTREAM SIDE OF THE AIR FLOW; WHEREBY FLOW OF FUEL THROUGH THE CONDUIT EXITS INTO THE AIR STREAM AT THE VERTEX FORMING A COMBUSTIBLE MIXTURE THAT IS CARRIED OVER THE SURFACE OF THE UPSTREAM BODY TO THE GAP AREA TO REPLENISH THE MIXTURE OF GASES WITHIN THE GAP ESTABLISHING A STABLE RECIRCULATION ZONE AT A PILOTING FLAME.
US222853A 1972-02-02 1972-02-02 Low drag flameholder Expired - Lifetime US3913319A (en)

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Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1997017574A1 (en) * 1995-11-07 1997-05-15 Westinghouse Electric Corporation Gas turbine combustor with enhanced mixing fuel injectors
EP1457738A2 (en) * 2003-03-13 2004-09-15 United Technologies Corporation Afterburner
US20040226298A1 (en) * 2003-05-13 2004-11-18 Snyder Timothy S. Augmentor pilot nozzle
US20080196414A1 (en) * 2005-03-22 2008-08-21 Andreadis Dean E Strut cavity pilot and fuel injector assembly
RU2444639C1 (en) * 2010-10-25 2012-03-10 Российская Федерация, от имени которой выступает Министерство промышленности и торговли Российской Федерации Минпромторг России Self-ignition of fuel mix in ramjet engine
GB2486545A (en) * 2010-12-17 2012-06-20 Gen Electric Aerodynamically enhanced fuel nozzle with rounded and straight sections
RU2544105C1 (en) * 2013-10-03 2015-03-10 Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения им. П.И. Баранова" High speed ramjet engine
RU2543915C1 (en) * 2013-10-03 2015-03-10 Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения им. П.И. Баранова" Fuel mix ignition in high-rate air jet engine

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2625795A (en) * 1946-02-26 1953-01-20 Thermal Res And Engineering Co Combustion stabilization means for high-velocity air streams having a pilot burner and a streamline igniter grill
US2692480A (en) * 1948-05-07 1954-10-26 Onera (Off Nat Aerospatiale) Supersonic internal circulation combustion chamber, in particular combustion chamber for aircraft jet engines
US2715813A (en) * 1952-04-14 1955-08-23 Frederick T Holmes Fuel injector and flame holder
US2955419A (en) * 1951-12-10 1960-10-11 Phillips Petroleum Co Flame holder device
US3300976A (en) * 1964-02-21 1967-01-31 Rolls Royce Combined guide vane and combustion equipment for bypass gas turbine engines
US3328958A (en) * 1963-06-05 1967-07-04 United Aircraft Corp Aerodynamic-type flameholder
US3455108A (en) * 1966-02-28 1969-07-15 Technology Uk Combustion devices
US3465525A (en) * 1966-03-25 1969-09-09 Rolls Royce Gas turbine bypass engines
US3605407A (en) * 1968-06-10 1971-09-20 Technology Uk Combustion devices
US3701255A (en) * 1970-10-26 1972-10-31 United Aircraft Corp Shortened afterburner construction for turbine engine

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2625795A (en) * 1946-02-26 1953-01-20 Thermal Res And Engineering Co Combustion stabilization means for high-velocity air streams having a pilot burner and a streamline igniter grill
US2692480A (en) * 1948-05-07 1954-10-26 Onera (Off Nat Aerospatiale) Supersonic internal circulation combustion chamber, in particular combustion chamber for aircraft jet engines
US2955419A (en) * 1951-12-10 1960-10-11 Phillips Petroleum Co Flame holder device
US2715813A (en) * 1952-04-14 1955-08-23 Frederick T Holmes Fuel injector and flame holder
US3328958A (en) * 1963-06-05 1967-07-04 United Aircraft Corp Aerodynamic-type flameholder
US3300976A (en) * 1964-02-21 1967-01-31 Rolls Royce Combined guide vane and combustion equipment for bypass gas turbine engines
US3455108A (en) * 1966-02-28 1969-07-15 Technology Uk Combustion devices
US3465525A (en) * 1966-03-25 1969-09-09 Rolls Royce Gas turbine bypass engines
US3605407A (en) * 1968-06-10 1971-09-20 Technology Uk Combustion devices
US3701255A (en) * 1970-10-26 1972-10-31 United Aircraft Corp Shortened afterburner construction for turbine engine

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1997017574A1 (en) * 1995-11-07 1997-05-15 Westinghouse Electric Corporation Gas turbine combustor with enhanced mixing fuel injectors
EP1457738A3 (en) * 2003-03-13 2006-05-10 United Technologies Corporation Afterburner
EP1457738A2 (en) * 2003-03-13 2004-09-15 United Technologies Corporation Afterburner
US20040177616A1 (en) * 2003-03-13 2004-09-16 Buey John R Augmentor
US6968694B2 (en) * 2003-03-13 2005-11-29 United Technologies Corporation Augmentor
US20040226298A1 (en) * 2003-05-13 2004-11-18 Snyder Timothy S. Augmentor pilot nozzle
US6971239B2 (en) * 2003-05-13 2005-12-06 United Technologies Corporation Augmentor pilot nozzle
US20080196414A1 (en) * 2005-03-22 2008-08-21 Andreadis Dean E Strut cavity pilot and fuel injector assembly
RU2444639C1 (en) * 2010-10-25 2012-03-10 Российская Федерация, от имени которой выступает Министерство промышленности и торговли Российской Федерации Минпромторг России Self-ignition of fuel mix in ramjet engine
GB2486545A (en) * 2010-12-17 2012-06-20 Gen Electric Aerodynamically enhanced fuel nozzle with rounded and straight sections
US8387391B2 (en) 2010-12-17 2013-03-05 General Electric Company Aerodynamically enhanced fuel nozzle
GB2486545B (en) * 2010-12-17 2017-08-16 Gen Electric Aerodynamically enhanced fuel nozzle
RU2544105C1 (en) * 2013-10-03 2015-03-10 Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения им. П.И. Баранова" High speed ramjet engine
RU2543915C1 (en) * 2013-10-03 2015-03-10 Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения им. П.И. Баранова" Fuel mix ignition in high-rate air jet engine

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