US3605407A - Combustion devices - Google Patents

Combustion devices Download PDF

Info

Publication number
US3605407A
US3605407A US830471A US3605407DA US3605407A US 3605407 A US3605407 A US 3605407A US 830471 A US830471 A US 830471A US 3605407D A US3605407D A US 3605407DA US 3605407 A US3605407 A US 3605407A
Authority
US
United States
Prior art keywords
vane
recesses
flow
recess
downstream
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
US830471A
Inventor
William Dean Bryce
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.)
TECHNOLOGY UK
Original Assignee
TECHNOLOGY UK
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 TECHNOLOGY UK filed Critical TECHNOLOGY UK
Application granted granted Critical
Publication of US3605407A publication Critical patent/US3605407A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • 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

Definitions

  • the vane of aerofoil section has recesses of generally elliptical shape in its side surfaces. Separation of flow round the vane occurs at the resultant discontinuities and causes recirculation within the recesses, the length of which ensures reduction in velocity compared with free stream flow to allow adequate mixing between unburnt fuel/air mixture and combustion gases.
  • an inlet is provided in the leading edge of the vane for gas which is discharged from slots positioned rearwardly of the recesses as a cooling film over the downstream surfaces of the vane.
  • the surfaces of the recesses may be of ceramic (e.g., silicon nitride) or other refractory material.
  • the present invention relates to combustion devices wherein a flame stabilisation zone is formed in a swiftly moving gas stream by the separation of flow from the surface of a body disposed within the stream.
  • baflles In aircraft gas turbine jet propulsion engines, extra power can be developed by burning additional fuel in an afterburner. It has long been the practice in such installations to use fixed baflles to produce stable turbulent (or recirculation) zones in their wakes wherein flames will maintain themselves. Such baffles offer undesirable resistance to flow during such time as afterburning is not in operation.
  • One of the more common forms of fixed bafile is a V-shaped gutter having its apex pointing up stream of the flow, the extreme simplicity of the arrangement tending to outweigh adverse considerations. By setting the arms to an included angle of the order of 45, or slightly less according to flow velocity, a reasonable optimum between resistance and the provision of an adequate recirculation zone can be obtained.
  • baffie resistance can be critical in determining the total amount of afterburning which can be employed, and an afterburner system having a lower pressure loss when in the non-operating condition is desirable, provided that the penalties arising out of other considerations are not too severe.
  • the present invention is concerned with means directed towards this end, as are prior co-pending US. patent application Ser. No. 780,085, filed on Aug. 5, 1968, by L. D. Wigg, now U.S. Pat. No. 3,504,491, and co-pending US. patent applications Ser. Nos. 830,259 and 830,394, filed coincidentally herewith by the present applicant.
  • the turbulence can, by suitable shaping of the recess, be contained within the recess or subtantially so to give a stable recirculation zone, the flow over the surface becoming re-attached downstream of the recess.
  • One such arrangement is the so-called vortex hearing in which a near circular recess is formed in a surface with two opposed cusp portions spaced from one another in the direction of flow, a zone of rotating fluid forming in the recess so that part of its periphery defines a 3,605,407 Patented Sept.
  • velocities at the periphery of the recess would be of the same order as the freestream velocity which will be too high to allow for complete combustion of fuel/ air mixtures in the recirculation zone.
  • the peripheral velocities are reduced which incidentally improves the mixing characteristics. Further improvement can be obtained by varying the shape of the junctions between the recess and the surface.
  • a combustion device comprises a body having an aerodynamic surface and a recess formed in the surface, the recess being arranged to sustain a recirculating flow and shaped to induce a gas flow over the surface to separate therefrom and mix at least in part with the recirculating flow.
  • the recirculating flow is contained partially within the recess which is dimensioned to maintain the peripheral velocity of the recirculating flow at less than the free-stream velocity of the gas flow over the surface.
  • the body is a vane of symmetrical aerofoil section having recesses in its opposite surfaces in the region of maximum thickness of the vane.
  • a cooling stream may be introduced into the vane and discharged as thin films over the surfaces of the vane downstream of the recesses.
  • FIG. 1 is an axial section through an aerofoil section vane
  • FIG. 2 is a similar view of another vane
  • FIG. 3 shows a modification to the vane of FIG. 2.
  • FIG. 1 shows a vane 1 of symmetrical aerofoil section which is intended to be mounted, for example, in an afterburner duct extending between the exhaust of a gas turbine and a propulsion nozzle, the direction of gas flow over the vane being indicated by the arrows B.
  • the opposite surfaces of the vane are cut away in the region of maximum vane thickness to form recesses 2, 3 of part elliptical section as shown in the drawing, the edges of the recesses extending along the vane transversely of the direction of gas flow and being undercut to define opposed cusp portions 4, 5 spaced from one another in the direction of gas flow. Flow over the vane surfaces will separate at the upstream cusp portions 4 and re-attach in the vicinities of the downstream cusp portions 5, the profile of the after portion of the vane being such that little or no wake will result.
  • FIG. 2 shows a vane 6 having recesses 7, 8 in its opposite surfaces in tWhlCh the upstream cusp portions have been omitted to give a bluff body type of separation point with consequent increase in turbulence and thus improved mixing.
  • the inner surfaces 9, 10 of the recesses are substantially fiat while the downstream cusp portions of the previous vane are replaced by inclined surfaces 11, 12 subtending an angle of 30 with the inner surfaces 9, 10'.
  • the stagnation point of the reattaching flow should be at or near the downstream corners of the faces 11, 12 and to achieve this, the vane thickness increases steadily from the leading edge to the upstream steps of the recesses 7, 8.
  • the surfaces of the recesses and the after parts of the vanes are exposed to hot gases and it may be desirable to provide for some cooling of these.
  • FIG. 3 shows a vane of composite construction having a solid afterbody 13 and a hollow nose portion 14.
  • the nose portion is shaped to define recesses 7, 8 as in the embodiment last described and likewise has flat surfaces 9, 10 and inclined faces 11, 12.
  • An upstream-facing opening 15 is provided in the leading edge of the nose section 14 and apertures 16, 17 are formed between the nose section and the afterbody 13. Gas will enter the nose section from the main flow through the opening 15 as indicated by the arrow B and pass over the inside surfaces of the recesses 7, 8 before passing through the apertures 16, 17, as indicated by the arrows O, to be discharged therefrom tangentially over the afterbody surfaces. Heat is thus drawn from the recesses and a cooling film is formed around the afterbody.
  • Film cooling of the outer surfaces of the recesses is not a practicable proposition in view of the possibility of quenching the combustion taking place in the recirculation gases.
  • these surfaces are of ceramic (for example, silicon nitride), or other refractory material.
  • Atomised fuel is preferably discharged into the main flow so that it impinges on the vane surfaces downstream of the opening 15 but upstream of the recesses 7,
  • the opening 15 may be dispensed with and cooling flow introduced to the interior of the nose portion by connection to some suitable fuel-free point.
  • Flame stabilisers as described herein are not restricted to use in afterburners, but may be used also, for example, in by-pass ducts of turbofan engines where it is desired to produce extra power intermittently by burning fuel in such ducts.
  • a combustion device for producing a flame stabilization zone in a swiftly moving gas stream comprising a vane of symmetrical airfoil section with recesses formed in opposite surfaces of said vane in the region of maximum thickness thereof to sustain a recirculating flow, said recesses being shaped to induce gas flow over said vane surfaces to separate therefrom and mix at least in part with said recirculating flow, wherein each recess is substantially of part elliptical section with edges extending along said vane transversely of the direction of gas flow.
  • a combination device for producing a flame stabilization zone in a swiftly moving gas stream comprising a vane of symmetrical airfoil section with recesses formed in opposite surfaces of said vane in the region of maximum thickness thereof to sustain a recirculating flow, said recesses being shaped to induce gas flow over said vane surfaces to separate therefrom and mix at least in part with said recirculating flow, wherein each recess includes a substantially flat surface of refractory material extending generally parallel to the direction of free-stream gas flow over said vane.
  • a combustion device according to claim 1, wherein said recesses are dimensioned to maintain the peripheral velocity of said recirculating flow at less than the freestream velocity of the gas flow over said surface and to contain said recirculating flow partially within said recesses.
  • a combustion device according to claim 1, wherein said edges are undercut to define opposed cusp portions spaced from one another in the direction of intended gas flow over said vane.
  • a combustion device wherein said substantially flat surface is connected at its downstream extremity to said vane surface by an inclined surface extending in a generally downstream direction.
  • a combustion device according to claim 5, wherein said inclined surface subtends an angle of the order of 30 with said substantially flat surface.
  • a combustion device wherein said refractory material is a ceramic.
  • a combustion device wherein said refractory material is silicon nitride.
  • a combustion device including means within said body for extraction of heat from said recesses.
  • a combustion device including a passage within said body for the flow of fluid coolant.
  • a combustion device including a hollow portion embracing said region of maxi mum thickness and provided with openings for entry and exit of fluid coolant.
  • a combustion device having an upstream-facing opening connected to the hollowportion, said exit openings being formed in the surface of said vane downstream of the recesses.
  • a combustion device in which the exit openings are arranged to discharge fluid tangentially downstream over the vane surfaces.
  • a combustion device wherein said recesses are dimensioned to maintain the peripheral velocity of said recirculating flow at less than the free stream velocity of the gas flow over said surface and to contain said recirculating flow partially within said recesses.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Combustion Of Fluid Fuel (AREA)

Abstract

THE VANE OF AEROFOIL SECTION HAS RECESSES OF GENERALLY ELLIPTICAL SHAPE IN ITS SIDE SURFACES. SEPARATION OF FLOW ROUND THE VANE OCCURS AT THE RESULTANT DISCONTINUITIES AND CAUSES RECIRCULATION WITHIN THE RECESSES, THE LENGTH OF WHICH ENSURES REDUCTION IN VELOCITY COMPARED WITH FREE STREAM FLOW TO ALLOW ADEQUATE MIXING BETWEEN UNBURNT FUEL/AIR MIXTURE AND COMBUSTION GASES. IN ONE ARRANGEMENT, AN INLET IS PROVIDED IN THE LEADING EDGE OF THE VANE FOR GAS WHICH IS DISCHARGED FROM SLOTS POSITIONED REARWARDLY OF THE RECESSES AS A COOLING FILM OVER THE DOWNSTREAM SURFACES OF THE VANE. THE SURFACES OF THE RECESSES MAY BE OF CERAMIC (E.G., SILICON NITRIDE) OR OTHER REFRACTORY MATERIAL.

Description

p 20, 1971 w. o. BRYCE 3,605,407
counus'non nnvxcms F1196 Juno 4, 1969 United States Patent US. Cl. 6039.72 14 Claims ABSTRACT OF THE DISCLOSURE The vane of aerofoil section has recesses of generally elliptical shape in its side surfaces. Separation of flow round the vane occurs at the resultant discontinuities and causes recirculation within the recesses, the length of which ensures reduction in velocity compared with free stream flow to allow adequate mixing between unburnt fuel/air mixture and combustion gases. In one arrangement, an inlet is provided in the leading edge of the vane for gas which is discharged from slots positioned rearwardly of the recesses as a cooling film over the downstream surfaces of the vane. The surfaces of the recesses may be of ceramic (e.g., silicon nitride) or other refractory material.
The present invention relates to combustion devices wherein a flame stabilisation zone is formed in a swiftly moving gas stream by the separation of flow from the surface of a body disposed within the stream.
In aircraft gas turbine jet propulsion engines, extra power can be developed by burning additional fuel in an afterburner. It has long been the practice in such installations to use fixed baflles to produce stable turbulent (or recirculation) zones in their wakes wherein flames will maintain themselves. Such baffles offer undesirable resistance to flow during such time as afterburning is not in operation. One of the more common forms of fixed bafile is a V-shaped gutter having its apex pointing up stream of the flow, the extreme simplicity of the arrangement tending to outweigh adverse considerations. By setting the arms to an included angle of the order of 45, or slightly less according to flow velocity, a reasonable optimum between resistance and the provision of an adequate recirculation zone can be obtained.
Nevertheless, baffie resistance can be critical in determining the total amount of afterburning which can be employed, and an afterburner system having a lower pressure loss when in the non-operating condition is desirable, provided that the penalties arising out of other considerations are not too severe. The present invention is concerned with means directed towards this end, as are prior co-pending US. patent application Ser. No. 780,085, filed on Aug. 5, 1968, by L. D. Wigg, now U.S. Pat. No. 3,504,491, and co-pending US. patent applications Ser. Nos. 830,259 and 830,394, filed coincidentally herewith by the present applicant.
Fluid flowing over a surface in which there is a discontinuity will separate frpm the surface and turbulence will result. If the discontinuity is in the form of a recess in the surface, the turbulence can, by suitable shaping of the recess, be contained within the recess or subtantially so to give a stable recirculation zone, the flow over the surface becoming re-attached downstream of the recess. One such arrangement is the so-called vortex hearing in which a near circular recess is formed in a surface with two opposed cusp portions spaced from one another in the direction of flow, a zone of rotating fluid forming in the recess so that part of its periphery defines a 3,605,407 Patented Sept. 20, 1971 boundary for fluid flowing along the surface which takes the place of a solid boundary wall at the discontinuity. Neglecting friction and boundary layer effects, there will be no velocity discontinuity at the separation point and hence the flow will re-attach downstream of the cusp recess without significant wake.
With such an arrangement, velocities at the periphery of the recess would be of the same order as the freestream velocity which will be too high to allow for complete combustion of fuel/ air mixtures in the recirculation zone. However, by lengthening the recess so that it becomes substantially elliptical, the peripheral velocities are reduced which incidentally improves the mixing characteristics. Further improvement can be obtained by varying the shape of the junctions between the recess and the surface.
Since the surface downstream of the recess will almost certainly be exposed to hot gases, it would be advantageous to provide cooling means in this region.
A combustion device according to the invention comprises a body having an aerodynamic surface and a recess formed in the surface, the recess being arranged to sustain a recirculating flow and shaped to induce a gas flow over the surface to separate therefrom and mix at least in part with the recirculating flow.
Preferably, the recirculating flow is contained partially within the recess which is dimensioned to maintain the peripheral velocity of the recirculating flow at less than the free-stream velocity of the gas flow over the surface.
Preferably also, the body is a vane of symmetrical aerofoil section having recesses in its opposite surfaces in the region of maximum thickness of the vane.
According to a feature of the invention, a cooling stream may be introduced into the vane and discharged as thin films over the surfaces of the vane downstream of the recesses.
Some embodiments of the invention will now be described by way of example with reference to the accompanying diagrammatic drawings of which:
FIG. 1 is an axial section through an aerofoil section vane,
FIG. 2 is a similar view of another vane, and
FIG. 3 shows a modification to the vane of FIG. 2.
FIG. 1 shows a vane 1 of symmetrical aerofoil section which is intended to be mounted, for example, in an afterburner duct extending between the exhaust of a gas turbine and a propulsion nozzle, the direction of gas flow over the vane being indicated by the arrows B.
The opposite surfaces of the vane are cut away in the region of maximum vane thickness to form recesses 2, 3 of part elliptical section as shown in the drawing, the edges of the recesses extending along the vane transversely of the direction of gas flow and being undercut to define opposed cusp portions 4, 5 spaced from one another in the direction of gas flow. Flow over the vane surfaces will separate at the upstream cusp portions 4 and re-attach in the vicinities of the downstream cusp portions 5, the profile of the after portion of the vane being such that little or no wake will result. As a result of flow separation, recirculation will occur within the recesses and, with a ratio between major and minor axes of the order of 3/1 or greater, the velocity of the recirculation flow at the periphery of the recess will be less than that of the freestream flow over the vane. If a fuel/ air mixture is introduced into the flow and ignited by conventional means, flame stabilisation zones will be set up in the recesses and the difference in the peripheral and free-stream flows will enable mixing to take place between incoming unburned mixture and the hot burnt products from the recirculation zone.
FIG. 2 shows a vane 6 having recesses 7, 8 in its opposite surfaces in tWhlCh the upstream cusp portions have been omitted to give a bluff body type of separation point with consequent increase in turbulence and thus improved mixing. The inner surfaces 9, 10 of the recesses are substantially fiat while the downstream cusp portions of the previous vane are replaced by inclined surfaces 11, 12 subtending an angle of 30 with the inner surfaces 9, 10'. For best performance the stagnation point of the reattaching flow should be at or near the downstream corners of the faces 11, 12 and to achieve this, the vane thickness increases steadily from the leading edge to the upstream steps of the recesses 7, 8.
In the foregoing embodiments, the surfaces of the recesses and the after parts of the vanes are exposed to hot gases and it may be desirable to provide for some cooling of these.
FIG. 3 shows a vane of composite construction having a solid afterbody 13 and a hollow nose portion 14. The nose portion is shaped to define recesses 7, 8 as in the embodiment last described and likewise has flat surfaces 9, 10 and inclined faces 11, 12. An upstream-facing opening 15 is provided in the leading edge of the nose section 14 and apertures 16, 17 are formed between the nose section and the afterbody 13. Gas will enter the nose section from the main flow through the opening 15 as indicated by the arrow B and pass over the inside surfaces of the recesses 7, 8 before passing through the apertures 16, 17, as indicated by the arrows O, to be discharged therefrom tangentially over the afterbody surfaces. Heat is thus drawn from the recesses and a cooling film is formed around the afterbody. Film cooling of the outer surfaces of the recesses is not a practicable proposition in view of the possibility of quenching the combustion taking place in the recirculation gases. Preferably, these surfaces are of ceramic (for example, silicon nitride), or other refractory material. Atomised fuel is preferably discharged into the main flow so that it impinges on the vane surfaces downstream of the opening 15 but upstream of the recesses 7,
'8, as, for instance, by spray nozzles 18, 19. Alternatively, the opening 15 may be dispensed with and cooling flow introduced to the interior of the nose portion by connection to some suitable fuel-free point.
The performance of such a flame stabiliser would be comparable, from the combustion point of view, with that of a V-gutter of width equal to the combined depth of the recesses. The blockage of the duct will thus be of the order of 2 to 3 times that of the gutter but without the large wake resulting therefrom and the pressure loss when afterburning is not in operation will therefore be considerably lower.
Flame stabilisers as described herein are not restricted to use in afterburners, but may be used also, for example, in by-pass ducts of turbofan engines where it is desired to produce extra power intermittently by burning fuel in such ducts.
I claim:
1. A combustion device for producing a flame stabilization zone in a swiftly moving gas stream comprising a vane of symmetrical airfoil section with recesses formed in opposite surfaces of said vane in the region of maximum thickness thereof to sustain a recirculating flow, said recesses being shaped to induce gas flow over said vane surfaces to separate therefrom and mix at least in part with said recirculating flow, wherein each recess is substantially of part elliptical section with edges extending along said vane transversely of the direction of gas flow.
2. A combination device for producing a flame stabilization zone in a swiftly moving gas stream comprising a vane of symmetrical airfoil section with recesses formed in opposite surfaces of said vane in the region of maximum thickness thereof to sustain a recirculating flow, said recesses being shaped to induce gas flow over said vane surfaces to separate therefrom and mix at least in part with said recirculating flow, wherein each recess includes a substantially flat surface of refractory material extending generally parallel to the direction of free-stream gas flow over said vane.
3. A combustion device according to claim 1, wherein said recesses are dimensioned to maintain the peripheral velocity of said recirculating flow at less than the freestream velocity of the gas flow over said surface and to contain said recirculating flow partially within said recesses.
4. A combustion device according to claim 1, wherein said edges are undercut to define opposed cusp portions spaced from one another in the direction of intended gas flow over said vane.
5. A combustion device according to claim 2, wherein said substantially flat surface is connected at its downstream extremity to said vane surface by an inclined surface extending in a generally downstream direction.
6. A combustion device according to claim 5, wherein said inclined surface subtends an angle of the order of 30 with said substantially flat surface.
7. A combustion device according to claim 2, wherein said refractory material is a ceramic.
8. A combustion device according to claim 2, wherein said refractory material is silicon nitride.
9. A combustion device according to claim 2 including means within said body for extraction of heat from said recesses.
10. A combustion device according to claim 9 including a passage within said body for the flow of fluid coolant.
11. A combustion device according to claim 2, including a hollow portion embracing said region of maxi mum thickness and provided with openings for entry and exit of fluid coolant.
12. A combustion device according to claim 11 having an upstream-facing opening connected to the hollowportion, said exit openings being formed in the surface of said vane downstream of the recesses.
13. A combustion device according to claim 12 in which the exit openings are arranged to discharge fluid tangentially downstream over the vane surfaces.
14. A combustion device according to claim 2, wherein said recesses are dimensioned to maintain the peripheral velocity of said recirculating flow at less than the free stream velocity of the gas flow over said surface and to contain said recirculating flow partially within said recesses.
References Cited UNITED STATES PATENTS 2,823,519 2/ 1958 Spalding 60-39.72 2,978,868 4/1961 Puffer 60-261 3,264,822 8/ 1966 Lane 60-39.72
FOREIGN PATENTS 4 756,185 -8/ 1956 Great Britain 6039.7
DOUGLAS HART, Primary Examiner US. Cl. X.R. 431-350
US830471A 1968-06-10 1969-06-04 Combustion devices Expired - Lifetime US3605407A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB27395/68A GB1213215A (en) 1968-06-10 1968-06-10 Improvements in or relating to combustion devices

Publications (1)

Publication Number Publication Date
US3605407A true US3605407A (en) 1971-09-20

Family

ID=10258890

Family Applications (1)

Application Number Title Priority Date Filing Date
US830471A Expired - Lifetime US3605407A (en) 1968-06-10 1969-06-04 Combustion devices

Country Status (4)

Country Link
US (1) US3605407A (en)
DE (1) DE1929259A1 (en)
FR (1) FR2010612A1 (en)
GB (1) GB1213215A (en)

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3913319A (en) * 1972-02-02 1975-10-21 Us Navy Low drag flameholder
US3938325A (en) * 1972-11-11 1976-02-17 Motoren- Und Turbinen-Union Munchen Gmbh Aerodynamic flame holder
US6026644A (en) * 1993-04-07 2000-02-22 Hitachi, Ltd. Stabilizer for gas turbine combustors and gas turbine combustor equipped with the stabilizer
EP0999413A2 (en) * 1998-11-02 2000-05-10 General Electric Company Hybride combustor and fuel nozzle therefor
US20030152878A1 (en) * 1997-11-10 2003-08-14 Staffler Franz Josef Streamlined body and combustion apparatus
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
US20050026096A1 (en) * 2001-11-23 2005-02-03 Staffler Franz Josef Streamlined body and combustion apparatus having such a streamlined body
WO2007096294A1 (en) * 2006-02-22 2007-08-30 Siemens Aktiengesellschaft A swirler for use in a burner of a gas turbine engine
US20080196414A1 (en) * 2005-03-22 2008-08-21 Andreadis Dean E Strut cavity pilot and fuel injector assembly
WO2008127467A2 (en) * 2006-12-15 2008-10-23 State Of Franklin Innovation, Llc Ceramic-encased hot surface igniter system for jet engines
US20100074757A1 (en) * 2008-09-25 2010-03-25 Paul Headland Swirler vane

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4309131A1 (en) * 1993-03-22 1994-09-29 Abb Management Ag Method and appliance for influencing the wake in furnace fittings
US5647215A (en) * 1995-11-07 1997-07-15 Westinghouse Electric Corporation Gas turbine combustor with turbulence enhanced mixing fuel injectors
CN110081463A (en) * 2019-01-18 2019-08-02 西北工业大学 A kind of flameholder premixed with edge of a wing turbulence structure

Cited By (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3913319A (en) * 1972-02-02 1975-10-21 Us Navy Low drag flameholder
US3938325A (en) * 1972-11-11 1976-02-17 Motoren- Und Turbinen-Union Munchen Gmbh Aerodynamic flame holder
US6026644A (en) * 1993-04-07 2000-02-22 Hitachi, Ltd. Stabilizer for gas turbine combustors and gas turbine combustor equipped with the stabilizer
US20030152878A1 (en) * 1997-11-10 2003-08-14 Staffler Franz Josef Streamlined body and combustion apparatus
US8979525B2 (en) * 1997-11-10 2015-03-17 Brambel Trading Internacional LDS Streamlined body and combustion apparatus
EP0999413A2 (en) * 1998-11-02 2000-05-10 General Electric Company Hybride combustor and fuel nozzle therefor
EP0999413A3 (en) * 1998-11-02 2002-07-03 General Electric Company Hybride combustor and fuel nozzle therefor
US20050026096A1 (en) * 2001-11-23 2005-02-03 Staffler Franz Josef Streamlined body and combustion apparatus having such a streamlined body
EP1457738A3 (en) * 2003-03-13 2006-05-10 United Technologies Corporation Afterburner
US6968694B2 (en) * 2003-03-13 2005-11-29 United Technologies Corporation Augmentor
US20040177616A1 (en) * 2003-03-13 2004-09-16 Buey John R Augmentor
AU2004200934B2 (en) * 2003-03-13 2006-05-25 United Technologies Corporation Augmentor
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
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
US20090025395A1 (en) * 2006-02-22 2009-01-29 Ulf Nilsson Swirler for Use in a Burner of a Gas Turbine Engine
US8302404B2 (en) 2006-02-22 2012-11-06 Siemens Aktiengesellschaft Swirler for use in a burner of a gas turbine engine
WO2007096294A1 (en) * 2006-02-22 2007-08-30 Siemens Aktiengesellschaft A swirler for use in a burner of a gas turbine engine
WO2008127467A2 (en) * 2006-12-15 2008-10-23 State Of Franklin Innovation, Llc Ceramic-encased hot surface igniter system for jet engines
WO2008127467A3 (en) * 2006-12-15 2009-04-30 State Of Franklin Innovation L Ceramic-encased hot surface igniter system for jet engines
US20100074757A1 (en) * 2008-09-25 2010-03-25 Paul Headland Swirler vane
EP2169304A1 (en) * 2008-09-25 2010-03-31 Siemens Aktiengesellschaft Swirler vane
US8579214B2 (en) 2008-09-25 2013-11-12 Siemens Aktiengesellschaft Swirler vane

Also Published As

Publication number Publication date
GB1213215A (en) 1970-11-25
FR2010612A1 (en) 1970-02-20
DE1929259A1 (en) 1969-12-18

Similar Documents

Publication Publication Date Title
US3605407A (en) Combustion devices
US3765178A (en) Afterburner flameholder
JP3703863B2 (en) Swirl mixer for combustor and method for burning fuel and air in combustor
US3299632A (en) Combustion chamber for a gas turbine engine
US3455108A (en) Combustion devices
US8011188B2 (en) Augmentor with trapped vortex cavity pilot
EP1605207B1 (en) Thrust augmentor for gas turbine engines
US5791148A (en) Liner of a gas turbine engine combustor having trapped vortex cavity
US3906718A (en) Combustion apparatus for gas turbine engines
US3931707A (en) Augmentor flameholding apparatus
US5461866A (en) Gas turbine engine combustion liner float wall cooling arrangement
US2934889A (en) Noise abatement means
US4050241A (en) Stabilizing dimple for combustion liner cooling slot
EP0984152A2 (en) Tabbed nozzle for jet noise suppression
US2912821A (en) Valveless inlet for pulse jet
EP1764555A2 (en) Augmentor radial fuel spray bar with counterswirling heat shield
JP2000145475A (en) Jet noise suppressor for gas turbine engine
US2541171A (en) Air inlet structure for combustion chambers
US5339622A (en) Gas turbine engine with improved water ingestion prevention
EP2400221B1 (en) Ejector purge of cavity adjacent exhaust flowpath
US3817690A (en) Combustion devices
US3921391A (en) Combustor wing vortex generators
CN108253456B (en) Swirl afterburner based on outer concave cavity
US2709337A (en) Boundary layer control for the diffuser of a gas turbine
US2948117A (en) Afterburner flameholder