US2872785A - Jet engine burner apparatus having means for spreading the pilot flame - Google Patents
Jet engine burner apparatus having means for spreading the pilot flame Download PDFInfo
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- US2872785A US2872785A US230212A US23021251A US2872785A US 2872785 A US2872785 A US 2872785A US 230212 A US230212 A US 230212A US 23021251 A US23021251 A US 23021251A US 2872785 A US2872785 A US 2872785A
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- channel
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- linear
- pilot burner
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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
Definitions
- This invention relates to combustion apparatus and is particularly directed to combustion apparatus for jet engines.
- An object of the present invention comprises the provision of means for quickly spreading a pilot flame over primary ignition apparatus for igniting the main combustion mixture.
- a further object of the invention comprises the provision of means providing flame flow paths for the combustion flame to an annular secondary igniter structure disposed downstream of said primary structure.
- a still further object of the invention comprises the provision of combustion apparatus for a jet engine having a streamlined center body structure in which said apparatus comprises a pilot burner disposed completely within said center body structure and a cooling air flow path is provided between the inner walls of said center body structure and said pilot burner.
- Fig. 1 is a schematic axial section through a ram jet engine embodying the invention
- Fig. 2 is an enlarged view of a portion of Fig. 1 taken along line 22 of Fig. 3;
- Fig. 3 is an enlarged view taken along line 3 3 of Fig. 1;
- Fig. 4 is a sectional view taken along line 4-4 of Fig. 2;
- Fig. 5 is a view similar to Fig. 2 but of a modified form of the invention and taken along line 5-5 of Fig. 6;
- Fig. 6 is a view taken along line 66 of Fig. 5;
- Fig. 7 is a sectional view taken along line 77 of Fig. 5.
- a ram jet engine is schematically indicated by reference numeral 10, said engine comprising an open-ended duct 12.
- the duct 12 has a forwardly directed air entrance opening 16 and a streamlined center body 18 may be co-axially supported within said duct adjacent to its forward end.
- Various auxiliary equipment of the engine as for example fuel and oil pumps and their controls, are generally supported within the center body 18.
- the duct 12 also includes a combustion chamber 20 downstream of the center body 18 and a nozzle 22 is provided at the rear end of the duct 12 through which the combustion chamber gases discharge to provide the power plant wtih forward propulsive thrust.
- Fuel is supplied through a plurality of fuel nozzles 24 to provide a main combustible mixture for ignition in the combustion chamber 20.
- the center body 18 has a streamlined outer periphery and a pilot burner 26 is completely disposed therein at the downstream end of said center body.
- the pilot burner has a conical upstream end with a burner tube 28 extending therefrom, said burner tube preferably having a reduced diameter discharge end at the downstream end 2,872,785 Patented Feb. 10, 1959 '30 flows over the pilot burner tube 28 through the annular passage 34 and out the downstream end of the center-body. This latter air flow helps cool the pilot burner tube.
- Fuel is supplied to the pilot burner 26 through one or more fuel nozzles 36.
- the pilot burner also has a flame holder means 38 disposed across the upstream end of the pilot burner tube 28.
- said flame holder means comprises a disc with a plurality of swirl slots 44] therethrough and a central opening through which extends a suitable igniter 42, such as a spark plug.
- a suitable igniter 42 such as a spark plug.
- An annular channel member or gutter 44 is supported co-axially and downstream of the pilot burner and center body.
- the annular gutter 44 is disposed downstream of the center body 18 and the pilot burner 26 so as to minimize its drag effect on the fluid flowing through the duct 12.
- the annular gutter 44 has a V-shaped crosssection with the open side of its annular channel facing in a downstream direction.
- a plurality of circumferentially-spaced linear channel members or gutters 46 extend from the pilot burner tube 28 through the center body 18 to the annular gutter 44. Four such linear gutters 46 are illustrated and each such linear gutter has one end opening into the pilot burner tube 28 and has its other end opening into the annular gutter 44.
- the minimum radius of the annular gutter 44 is larger than the radius of the outer periphery of the discharge end of the pilot burner tube 28 so that the linear gutters 46 diverge in a downstream direction.
- Each linear gutter 46 has a generally V-shaped cross-section and the open channel side of each linear gutter faces in a generally inward and downstream direction so that the combustible fluid flows over each said linear gutter from its apex.
- a second or secondary annular channel member or gutter 48 is co-axially disposed downstream of the first or primary annular gutter 44.
- Said secondary annular gutter 48 has a V-shaped cross-section with its open channel side facing downstream and is disposed a substantial distance downstream of the primary annular gutter 44, preferably axially downstream of a point at which the turbulence of the main combustible mixture created by said primary gutter begins to fall 01f substantially.
- a second plurality of linear channel members or gutters 50 extend from the outer periphery of the primary annular gutter 44 to the secondary annular gutter 48, said gutters 50, like the gutters 46, being circumferentially-spaced for flow of a portion of the combustible mixture through the spaces between said gutters.
- each of said second or secondary linear gutters is in communication with the channel of primary annular gutter 44 and the other end of the channel of each of said secondary linear gutters is in communication with the channel of the secondary annular gutter 48.
- the secondary gutter 48 has a minimum radius larger than that of the radially outer periphery annular gutter 44 so that the secondary linear gutters 50 diverge in a downstream direction. The magnitude of this divergence is small so that each secondary linear gutter 50 extends in a generally downstream direction from the primary annular gutter 44.
- each secondary linear gutter 50 has a V-shaped cross-section with its open channel side facing inwardly.
- the pilot-burner 26 is supplied with sufficient fuel such that burning pilot fuel is propagated or spread out through the primary linear gutters 46 to the primary annular gutter 44.
- the burning pilot fuel discharging from the pilot burner and propagated along the primary linear gutters 46'to the primary annular gutter 44 is eflective to ignite the main combustible mixture flowing thereover.
- the secondary linear gutters 50 act to guide the flame of the burning combustible mixture from the primary annular gutter 44 to the secondary annular gutter 48 whereupon the annular gutter 4% acts as a secondary source of ignition for the main combustible mixture downstream of the primary ignition at the pilot burner 26, linear gutters 46, and annular gutter 44.
- each secondary annular gutter 48 is disposed a substantial axial distance downstream of the primary annular gutter 44 whereby each secondary linear gutter 50 has a substantial length in an axial direction. If each secondary linear gutter 50 makes no angle or only a small angle with the axis of the combustion apparatus described then flame will be propagated therealong at a steady rate from the primary annular gutter 44 to the secondary annular gutter 48. If, however, this angle is increased beyond a small value, for example beyond 10, then the flame propagated along each secondary gutter 50 will become unsteady, that is it will pulsate as a result of the turbulence created by the main combustible mixture flowing over said secondary linear gutter. The frequency of said flame pulsations apparently increases with an increase in said angle.
- each secondary linear gutter 50 makes with the axis of the combustion axis cannot be made large enough to avoid said low frequency flame pulsations since, as stated, the secondary annular gutter 43 should be disposed a substantial axial distance downstream of the primary annular gutter 44. Hence the angle between each secondary linear gutter 5t] and said axis is made small It has been found that for an aircraft jet engine this angle should be no more than approximately and preferably is within the range'of 4 to 7.
- the primary linear gutters 46 make an angle of approximately 30 with the axis of the combustion apparatus, suflicient fuel being supplied to the pilot burner 26 for propagation of a flame through said linear gutters 46 to the primary annular gutter 44.
- This angle of 30 is sufficiently large that the frequency of pulsation of the flame propagated along the primary linear gutters 46 is high enough not to be objectionable.
- the primary linear gutters 46 could be radial. With this latter arrangement, however, the plane of the primary annular gutter 44 would include the center body 18 and therefore the drag resistance of said gutter would be increased.
- a plurality of circumferentially spaced pilot burners may be provided in lieu of or in addition to said central pilot burner with each of such circumferentially-spaced pilot burners communicating directly with the primary annular gutter. Such an arrangement is illustrated in Figs. 5-7.
- Figs. 57 the parts corresponding to the parts of Figs. 1-4 have been indicated by like reference numerals but with a subscript a added thereto.
- the combustion apparatus of Figs. 5-7 is like that of Figs. 1-4 except a plurality of circumferentially-spaced pilot burners 60 have been added and in addition a duct 62 has been provided upstream of each linear gutter 46a for conducting air to the associated pilot burner 60 from the center body 18a.
- the center body 18a has slots '63 through which the ducts 62 open into the center body 1801.
- Each pilot burner 60 has a conical upstream end and a pilot burner tube 64 extend downstream therefrom.
- Each pilot burner 60 also has a fuel nozzle 66 for supplying fuel for mixture with said pilot burner air.
- Each pilot burner 60 also has a flame holder disc 68. If, as illustrated, a central pilot burner 26a is provided, then the auxiliary pilot burners 60 are ignited by the flame propagated from said central pilot burner along the gutters 46a so that no special igniter means is necessary for the auxiliary pilot burners.
- Each pilot burner tube 64 is interposed in the annular gutter 44a thereby dividing said annular gutter into sections of V-shaped cross-section so that said tubes 64 form part of said annular gutter.
- each pilot burner tube 64 has substantially opposed V-shaped slots in its wall from which the adjacent V-shaped sections of the annular gutter extend.
- each said V-shaped section of the gutter 44a at a pilot burner tube 64 is adjacent to the flame holder disc 68 of said tube and the sides of said V-shaped sections extend to the downstream end of said pilot burner tube whereby the V-shaped sections of the annular gutter 44a also act as flame cross-over tubes for propagating a pilot flame from one pilot burner 60 to the next for igniting said latter burner.
- This arrangement of a plurality of pilot burners with V-shaped gutters functioning as flame cross-over tubes is more fully disclosed in applicants co-pending application Serial No. 219,047, filed April 3, 1951.
- the remaining structure of Figs. 57 is essentially the same as that of Figs. 14. It should be noted that in Figs. 5-7 certain of the secondary linear gutters 50a extend downstream from the auxiliary pilot burners tubes 64 while the remainder of said gutters 50a extend downstream from the V-shaped sections of the annular gutter 44a.
- the jet engine has a centerbody structure 18 or 18a.
- a centerbody structure is not essential to a jet engine. If there is no such centerbody structure or if the air for the pilot burner or burners is not supplied through such a centerbody structure then in order to supply said air it is necessary to provide a duct or ducts extending upstream beyond the main fuel nozzles, for example as disclosed in said copending application.
- combustion apparatus having a combustion chamber and means for supplying a combustible mixture to said chamber; the combination therewith of means for igniting said main combustible mixture; said igniting means comprising pilot burner means including a burner tube from which the pilot flame emanates; annular channel means co-axial with said pilot burner tube and disposed within said chamber for flow of said mixture from a point upstream therefrom over the radially inner and outer annular sides of said annular channel means, said annular channel means having an open side facing downstream relative to said flow and having a diameter larger than the diameter of said pilot burner tube at its discharge end; and a plurality of linear channel members extending from said pilot burner tube to said annular channel means and being circumferentially-spaced about the axis of said annular channel means for flow of at least a portion of said mixture therebetween, each said linear channel member having an open side facing in the direction of the flow over said member and the channel of each linear channel member communicating at one end with said pilot burner tube and at its other end with the channel of
- combustion apparatus having a combustion chamber and means for supplying a main combustible mixture to said chamber; the combination therewith of means for igniting said main combustible mixture; said igniting means comprising first annular channel means disposed within said chamber across the flow path of said main combustible mixture for flow of said main mixture from a point upstream therefrom over the radially inner and outer annular sides of said annular channel means, said annular channel means having an open side facing in a downstream direction relative to said flow; pilot burner means having means for providing its own combustion mixture and communicating with said annular channel means for causing a pilot flame to extend into the channel of said annular channel means; second annular channel means.
- each linear channel member is inclined to the axis of said annular channel means by no more than approximately and in which at least the major portion of each annular channel means and each linear channel member has a V-shaped cross-section with its apex on its upstream side.
- combustion apparatus having a combustion chamber and means for supplying a main combustible mixture to said chamber; the combination therewith of means forigniting said main combustible mixture; said igniting means comprising a pilot burner disposed in said chamber and having means for providing its own combustible mixture; first annular channel means disposed within said chamber co-axial with and adjacent to the discharge end of said pilot burner and disposed across the flow path of said main combustible mixture for flow of said main mixture from a point upstream therefrom over.
- annular channel means having an open side facing in a downstream direction relative to said flow and having a radius larger than that of the discharge end of said pilot burner; a first plurality of linear channel members extending from said pilot burner to said first annular channel means, the channel of each of said linear channel members communicating at one end with said pilot burner and at its other end with the channel of said annular channel means; second annular channel means co-axially disposed downstream of said first annular channel means, said second annular channel means having a larger radius than said first annular channel means and having an open side facing in said downstream direction; and a plurality of second linear channel members each having one end communicating with the channel of said first annular channel means and having its other end communicating with the channel of said second annular channel means, each of said plurality of linear channel members being circumferentially-spaced about the axis of said annular channel means for flow of said main combustible mixture between said members and the channel of each said linear channel member being open on its downstream
- each said annular channel means and each said linear channel member has a V-shaped crossection with its apex on its upstream side.
- pilot burner includes a burner tube having an open discharge end of reduced diameter with said open discharge end facing in said downstream direction and with the downstream end of said first annular channel means being disposed downstream of said burner tube discharge end.
- combustion apparatus having a combustion chamber and means for supplying a main combustible mixture to said chamber; the combination therewith of means for igniting said main combustible mixture; said igniting means comprising first annular channel means disposed within said chamber for flow of said main mixture from a point upstream therefrom over the radially inner and outer sides of said annular channel means, said annular channel means having an open side facing in a downstream direction relative to said flow; a plurality of circumferentially-spaced pilot burners interposed in said annular channel means, each pilot burner having means for providing its own combustible mixture and having a burner tube with the open end of said burner tube being directed in said downstream direction and with each burner tube having a pair of slots in its side wall providing communication between said tube and the adjacent portions of the channel of said annular channel means; second annular channel means co axially disposed downstream of said first annular channel means, said second annular channel means having a radius larger than said first annular channel means and having an open side facing downstream relative to
- each annular channel means and each linear channel member diverges toward its open side and each pilot burner tube has flame holder means extending thereacross inwardly of the open end of said tube and adjacent to the apex of the adjacent portions of the channel of said first annular channel means and in which said linear channel members diverge in said downstream direction such that each linear channel member is inclined to the axis of said annular channel means by no more than 10.
- a jet engine including a duct, a center body coaxially disposed within said duct and having a streamlined outer periphery, a combustion chamber within said duct downstream of said center body and means for supplying a combustible mixture of air and fuel to said combustion chamber through the annular path about said center body; the combination therewith of means for igniting said combustible mixture for combustion in said chamber; said igniting means comprising a pilot burner co-axially disposed within said streamlined center body, said pilot burner including a burner tube having an open discharge end in which the discharge passage of said burner tube includes the entire cross-sectional area of the space between the outer walls of said tube at said discharge end; means for supplying fuel and air to said pilot burner tube; and a plurality of circumferentially-spaced means extending radially outwardly from said tube across the flow path of said combustible mixture for flow of said mixture thereover from a point upstream therefrom, said lastmentioned means communicating with said pilot burner tube for
- a jet engine including a duct, a center body coaxially disposed within said duct and having a streamlined outer periphery, a combustion chamber within said duct downstream of said center body, and means for supplying a combustible mixture of air and fuel to said combustion chamber through the annular path about said center body; the combination therewith of means for igniting said combustible mixture in said chamber; said igniting means comprising a pilot burner co-axially disposed within said center body and spaced from the surrounding wall of said center body to provide annular passage means therebetween, said pilot burner including a burner tube having an open discharge end disposed at the downstream end of said center body and in which the discharge passage of said burner tube includes the entire cross-sectional area of the space between the outer walls of said tube at said discharge end; means for supplying fuel and air into said center body to said pilot burner tube, a portion of said air flowing out through said annular passage means about the pilot burner for cooling said pilot burner; and a plurality of circumferentially-s
- a jet engine including a duct, a center body coaxially disposed within said duct and having a streamlined outer periphery, a combustion chamber within said duct downstream of said center body, and means for supplying a combustible mixture of air and fuel to said com- 8 bustion chamber through the annular path within said duct about said center body; the combination therewith of means for igniting said combustible mixture in 'said chamber; said igniting means comprising a pilot burner having a pilot burner tube co-axially disposed withinsaid center body and spaced from the surrounding wall of said center body to provide annular passage means therebetween, said pilot burner tube having a discharge-end of reduced diameter disposed at the downstream end of said center body; means for supplying air into said center body to said pilot burner, a portion of said air flowing out through said annular passage means about the pilot burner tube'for cooling said tube; annular channel means having its open side directed in a downstream direction, said annular channel means being co-axially disposed
- a jet engine including a duct, a center body coaxially disposed within said duct and having a streamlined outer periphery, a combustion chamber within said duct downstream of said center body, and means for supplying a combustible mixture of air and fuel to said combustion chamber through the annular path within said duct about said center body; the combination therewith of means for igniting said combustible mixture in said chamber; said igniting means comprising a pilot'burner having a pilot burner tube co-axially disposed within said center body and spaced from the surrounding Wall of said center body to provide annular passage means therebetween, said pilot burner tube having a discharge end of reduced diameter disposed at the downstream end of said center body; means for supplying air into said center body to said pilot burner, a portion of said air flowing out through said annular passage means about the pilot burner tube for cooling said tube; first annular channel means having its open channel side directed in a downstream direction relative to the flow of said combustible mixture, said annular channel means being co
- a jet engine including a duct, a center'body coaxially disposed within said duct and having a streamlined outer periphery, a combustion chamber downstream of said center body, and means for supplying a combustible mixture of air and fuel to said combustion chamber through the annular path about said center body; the combination therewith of means for igniting said combustible mixture for combustion in said chamber; said igniting means comprising a pilot burner co-axially disposed Within said streamlined center body, said pilot burner including a burner tube having an open discharge end of reduced diameter terminating at the downstream end of said center body; first annular channel means having its open side directed in a downstream direction, said annular channel means being co-axially disposed and extending downstream of the discharge end of said pilot burner tube and having a radius larger than that of the discharge end of the pilot burner tube; a first plurality of circumferentially-spaced linear channel members extending from said pilot burner tube to said annular channel means, the channel of each of said linear channel members communicating at
- a jet engine including a duct, a center body coaxially disposed within said duct, a combustion chamber downstream of said center body, and means for supplying a combustible mixture of air and fuel to said combustion chamber through the annular path about said center body; the combination therewith of means for igniting said combustible mixture for combustion in said chamber; said igniting means comprising a pilot burner co-axially disposed at the downstream end of said center body, said pilot burner including a burner tube; first annular channel means having its open side directed in a downstream direction, said annular channel means being co-axially disposed and extending downstream of the discharge end of said pilot burner tube and having a radius larger than that of the discharge end of the pilot burner tube; a first plurality of circumferentially-spaced linear channel members extending from said pilot burner tube to said annular channel means, the channel of each of said linear channel members communicating at one end with the pilot burner tube and at its other end with the channel of said annular channel means and the open channel side of each
- a jet engine including a duct, a center body co-axially disposed within said duct, a combustion chamber within said duct downstream of said center body, and
- said stabilizing means comprising means providing a sheltered chamber co-axially disposed at the downstream end of said center body and having an open downstream end; annular channel means having its open channel side directed in a downstream direction relative to flow of said combustible mixture, said annular channel means 'being co-axially disposed downstream of said chamber and having a diameter larger than the diameter of the downstream end of said chamber; and a plurality of circumferentially-spaced linear channel members extending from said chamber to said annular channel means, each of said linear channel members having the open side of its channel facing in said downstream direction and having its channel communicating at one end with said chamber and its other end with the channel of said annular channel means.
- a jet engine including a duct, a center body coaxially disposed within said duct, a combustion chamber within said duct downstream of said center body, and means for supplying a combustible mixture of air and fuel to said combustion chamber through the annular path about said center body; the combination therewith of means for stabilizing combustion within said chamber; said stabilizing means comprising means providing a sheltered chamber co-axially disposed at the downstream end of said center body and having an open downstream end; first annular channel means having its open channel side directed in a downstream direction relative to flow of said combustible mixture, said annular channel means being co-axially disposed downstream of said chamber and having a diameter larger than the diameter of the downstream end of said chamber; a first plurality of circumferentially-spaced linear channel members extending from said chamber to said annular channel means, each of said linear channel members having the open side of its channel facing in said downstream direction and having its channel communicating at one end with said chamber and its other end with the channel of said annular channel means; second annular channel
- a jet engine including a duct, a center body coaxially disposed within said duct, a combustion chamber within said duct downstream of said center body, and means for supplying a combustible mixture of air and fuel to said combustion chamber through the annular path about said center body; the combination therewith of means for stabilizing combustion within said chamber; said stabilizing means comprising means providing a sheltered chamberco-axially disposed at the downstream end of said center body and having an open downstream end; first annular channel means having its open channel side directed in a downstream direction relative to flow of said combustible mixture, said annular channel means being co-axially disposed downstream of said chamher and having a diameter larger than the diameter of the downstream end of said chamber; a first plurality of circumferentially-spaced linear channel members extending from said chamber to said annular channel means, each of said linear channel members having the open side of its channel facing .in said downstream direction and -havin1g its channel communicating at one end with said chamber andits other end with the channel of said stabil
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Description
Feb. 10, 1959 H. E. BARRETT ETAL NG MEANS FOR SPREADING THE PILOT FLAME 3 SheetsSheet 1 INVENTOREI HILLARD E. BARRETT: WILLIAM I PAYNE.
MM M
ATTORNEY Feb. 10, 1959 H. E. BARRETT ETAL 2,
JET ENGINE BURNER APPARATUS HAVING MEANS FOR SFREADING THE PILOT FLAME Filed June 6, 1951 3 Sheets-Sheet 2 L Afl l l gz ETT HI L WILLIAM F1 PAYNE.
ATTORNEY Feb. 10, 1959 H. E. BARRETT ETAL JET ENGINE BUR NER APPARATUS HAVING MEANS FOR SPREADING THE PILOT FLAME 3 Sheets-Sheet 3 Filed June 6, 1951 v n z 0R5 HILLARD E. BARRETT BYWILLIAM F. PAYNE.
Zfi A. ATTORNEY United States Patent JET ENGINE BURNER APPARATUS HAVING MEANS FOR SPREADING THE PILOT FLAME Hillard E. Barrett, East Orange, and William F. Payne,
Cedar Grove, N. 3., assignors to 'Curtiss-Wright Corporation, a corporation of Delaware Application June 6, 1951, Serial No. 230,212
19 Claims. (Cl. fill-39.72)
This invention relates to combustion apparatus and is particularly directed to combustion apparatus for jet engines.
The invention has been designed for use with jet engines in which maintenance of stable and eflicient combustion is diflicult particularly because of the high velocity of flow through the combustion chamber. An object of the present invention comprises the provision of means for quickly spreading a pilot flame over primary ignition apparatus for igniting the main combustion mixture. A further object of the invention comprises the provision of means providing flame flow paths for the combustion flame to an annular secondary igniter structure disposed downstream of said primary structure. A still further object of the invention comprises the provision of combustion apparatus for a jet engine having a streamlined center body structure in which said apparatus comprises a pilot burner disposed completely within said center body structure and a cooling air flow path is provided between the inner walls of said center body structure and said pilot burner.
Other objects of the invention will become apparent upon reading the annexed detailed description in connection with the drawing in which:
Fig. 1 is a schematic axial section through a ram jet engine embodying the invention;
Fig. 2 is an enlarged view of a portion of Fig. 1 taken along line 22 of Fig. 3;
Fig. 3 is an enlarged view taken along line 3 3 of Fig. 1;
Fig. 4 is a sectional view taken along line 4-4 of Fig. 2;
Fig. 5 is a view similar to Fig. 2 but of a modified form of the invention and taken along line 5-5 of Fig. 6;
Fig. 6 is a view taken along line 66 of Fig. 5; and
Fig. 7 is a sectional view taken along line 77 of Fig. 5.
Referring now to Figs. 1-4 of the drawing, a ram jet engine is schematically indicated by reference numeral 10, said engine comprising an open-ended duct 12. The duct 12 has a forwardly directed air entrance opening 16 and a streamlined center body 18 may be co-axially supported within said duct adjacent to its forward end. Various auxiliary equipment of the engine, as for example fuel and oil pumps and their controls, are generally supported within the center body 18. The duct 12 also includes a combustion chamber 20 downstream of the center body 18 and a nozzle 22 is provided at the rear end of the duct 12 through which the combustion chamber gases discharge to provide the power plant wtih forward propulsive thrust. Fuel is supplied through a plurality of fuel nozzles 24 to provide a main combustible mixture for ignition in the combustion chamber 20.
The center body 18 has a streamlined outer periphery and a pilot burner 26 is completely disposed therein at the downstream end of said center body. The pilot burner has a conical upstream end with a burner tube 28 extending therefrom, said burner tube preferably having a reduced diameter discharge end at the downstream end 2,872,785 Patented Feb. 10, 1959 '30 flows over the pilot burner tube 28 through the annular passage 34 and out the downstream end of the center-body. This latter air flow helps cool the pilot burner tube.
Fuel is supplied to the pilot burner 26 through one or more fuel nozzles 36. The pilot burner also has a flame holder means 38 disposed across the upstream end of the pilot burner tube 28. As illustrated said flame holder means comprises a disc with a plurality of swirl slots 44] therethrough and a central opening through which extends a suitable igniter 42, such as a spark plug. Thus the pilot burner flame burns in the tube 28 and discharges through the restricted downstream opening of said tube. The enlarged diameter upstream portion of the pilot burner tube 28 provides a region of relatively low velocity thereby adding to the stability of the pilot burner flame.
An annular channel member or gutter 44 is supported co-axially and downstream of the pilot burner and center body. The annular gutter 44 is disposed downstream of the center body 18 and the pilot burner 26 so as to minimize its drag effect on the fluid flowing through the duct 12. The annular gutter 44 has a V-shaped crosssection with the open side of its annular channel facing in a downstream direction. A plurality of circumferentially-spaced linear channel members or gutters 46 extend from the pilot burner tube 28 through the center body 18 to the annular gutter 44. Four such linear gutters 46 are illustrated and each such linear gutter has one end opening into the pilot burner tube 28 and has its other end opening into the annular gutter 44. The minimum radius of the annular gutter 44 is larger than the radius of the outer periphery of the discharge end of the pilot burner tube 28 so that the linear gutters 46 diverge in a downstream direction. Each linear gutter 46 has a generally V-shaped cross-section and the open channel side of each linear gutter faces in a generally inward and downstream direction so that the combustible fluid flows over each said linear gutter from its apex.
A second or secondary annular channel member or gutter 48 is co-axially disposed downstream of the first or primary annular gutter 44. Said secondary annular gutter 48 has a V-shaped cross-section with its open channel side facing downstream and is disposed a substantial distance downstream of the primary annular gutter 44, preferably axially downstream of a point at which the turbulence of the main combustible mixture created by said primary gutter begins to fall 01f substantially. A second plurality of linear channel members or gutters 50 extend from the outer periphery of the primary annular gutter 44 to the secondary annular gutter 48, said gutters 50, like the gutters 46, being circumferentially-spaced for flow of a portion of the combustible mixture through the spaces between said gutters. One end of the channel of each of said second or secondary linear gutters is in communication with the channel of primary annular gutter 44 and the other end of the channel of each of said secondary linear gutters is in communication with the channel of the secondary annular gutter 48. As illustrated, the secondary gutter 48 has a minimum radius larger than that of the radially outer periphery annular gutter 44 so that the secondary linear gutters 50 diverge in a downstream direction. The magnitude of this divergence is small so that each secondary linear gutter 50 extends in a generally downstream direction from the primary annular gutter 44. In addition each secondary linear gutter 50 has a V-shaped cross-section with its open channel side facing inwardly. Thus the portion of the combustible mixture flowing over the outer periphcry of the primary annular gutter 44 and over the radially inner edge of the secondary annular gutter 48 flows over each side of and between the circumferentially-spaced secondary linear gutters 50.
The pilot-burner 26 is supplied with sufficient fuel such that burning pilot fuel is propagated or spread out through the primary linear gutters 46 to the primary annular gutter 44. The burning pilot fuel discharging from the pilot burner and propagated along the primary linear gutters 46'to the primary annular gutter 44 is eflective to ignite the main combustible mixture flowing thereover. The secondary linear gutters 50 act to guide the flame of the burning combustible mixture from the primary annular gutter 44 to the secondary annular gutter 48 whereupon the annular gutter 4% acts as a secondary source of ignition for the main combustible mixture downstream of the primary ignition at the pilot burner 26, linear gutters 46, and annular gutter 44. It has been found that the addition of such a secondary annular gutter provides for smoother and more eflicient combustion. In addition since the secondary gutter 48 is disposed close to the wall of the combustion chamber 29 it tends to prevent the combustion flame from flashing back upstream from said gutter along the wall of the combustion chamber. Furthermore by disposing the annular gutters 44 and 48 in diflerent transverse planes instead of in a single transverse plane they oifer less drag resistance to the flow of the main combustible fluid.
As already stated, the secondary annular gutter 48 is disposed a substantial axial distance downstream of the primary annular gutter 44 whereby each secondary linear gutter 50 has a substantial length in an axial direction. If each secondary linear gutter 50 makes no angle or only a small angle with the axis of the combustion apparatus described then flame will be propagated therealong at a steady rate from the primary annular gutter 44 to the secondary annular gutter 48. If, however, this angle is increased beyond a small value, for example beyond 10, then the flame propagated along each secondary gutter 50 will become unsteady, that is it will pulsate as a result of the turbulence created by the main combustible mixture flowing over said secondary linear gutter. The frequency of said flame pulsations apparently increases with an increase in said angle. A high frequency of pilot flame pulsation is not too objectionable since it appears to attenuate itself but a low frequency of pulsation of the pilot flame causes rough combustion. The angle each secondary linear gutter 50 makes with the axis of the combustion axis cannot be made large enough to avoid said low frequency flame pulsations since, as stated, the secondary annular gutter 43 should be disposed a substantial axial distance downstream of the primary annular gutter 44. Hence the angle between each secondary linear gutter 5t] and said axis is made small It has been found that for an aircraft jet engine this angle should be no more than approximately and preferably is within the range'of 4 to 7.
At this point it should be noted that the primary linear gutters 46 make an angle of approximately 30 with the axis of the combustion apparatus, suflicient fuel being supplied to the pilot burner 26 for propagation of a flame through said linear gutters 46 to the primary annular gutter 44. This angle of 30 is sufficiently large that the frequency of pulsation of the flame propagated along the primary linear gutters 46 is high enough not to be objectionable. As far as said pilot flame propagation is concerned the primary linear gutters 46 could be radial. With this latter arrangement, however, the plane of the primary annular gutter 44 would include the center body 18 and therefore the drag resistance of said gutter would be increased.
If for some reason the quantity of fuel supplied to the central pilot burner 26 is insufficient to insure propagation of a flame to the primary annular gutter 44 then a plurality of circumferentially spaced pilot burners may be provided in lieu of or in addition to said central pilot burner with each of such circumferentially-spaced pilot burners communicating directly with the primary annular gutter. Such an arrangement is illustrated in Figs. 5-7.
In Figs. 57, the parts corresponding to the parts of Figs. 1-4 have been indicated by like reference numerals but with a subscript a added thereto. The combustion apparatus of Figs. 5-7 is like that of Figs. 1-4 except a plurality of circumferentially-spaced pilot burners 60 have been added and in addition a duct 62 has been provided upstream of each linear gutter 46a for conducting air to the associated pilot burner 60 from the center body 18a. For this purpose, the center body 18a has slots '63 through which the ducts 62 open into the center body 1801. Each pilot burner 60 has a conical upstream end and a pilot burner tube 64 extend downstream therefrom. Each pilot burner 60 also has a fuel nozzle 66 for supplying fuel for mixture with said pilot burner air. Each pilot burner 60 also has a flame holder disc 68. If, as illustrated, a central pilot burner 26a is provided, then the auxiliary pilot burners 60 are ignited by the flame propagated from said central pilot burner along the gutters 46a so that no special igniter means is necessary for the auxiliary pilot burners. Each pilot burner tube 64 is interposed in the annular gutter 44a thereby dividing said annular gutter into sections of V-shaped cross-section so that said tubes 64 form part of said annular gutter. Thus each pilot burner tube 64 has substantially opposed V-shaped slots in its wall from which the adjacent V-shaped sections of the annular gutter extend. The apex of each said V-shaped section of the gutter 44a at a pilot burner tube 64 is adjacent to the flame holder disc 68 of said tube and the sides of said V-shaped sections extend to the downstream end of said pilot burner tube whereby the V-shaped sections of the annular gutter 44a also act as flame cross-over tubes for propagating a pilot flame from one pilot burner 60 to the next for igniting said latter burner. This arrangement of a plurality of pilot burners with V-shaped gutters functioning as flame cross-over tubes is more fully disclosed in applicants co-pending application Serial No. 219,047, filed April 3, 1951. The remaining structure of Figs. 57 is essentially the same as that of Figs. 14. It should be noted that in Figs. 5-7 certain of the secondary linear gutters 50a extend downstream from the auxiliary pilot burners tubes 64 while the remainder of said gutters 50a extend downstream from the V-shaped sections of the annular gutter 44a.
In both modifications illustrated, the jet engine has a centerbody structure 18 or 18a. Such a centerbody structure, however, is not essential to a jet engine. If there is no such centerbody structure or if the air for the pilot burner or burners is not supplied through such a centerbody structure then in order to supply said air it is necessary to provide a duct or ducts extending upstream beyond the main fuel nozzles, for example as disclosed in said copending application.
While we have described our invention in detail in its present preferred embodiment, it will be obvious to those skilled in the art, after understanding our invention, that various changes and modifications may be made therein without departing from the spirit or scope thereof. We aim in the appended claims to cover all such modifications.
We claim as our invention:
1. In combustion apparatus having a combustion chamber and means for supplying a combustible mixture to said chamber; the combination therewith of means for igniting said main combustible mixture; said igniting means comprising pilot burner means including a burner tube from which the pilot flame emanates; annular channel means co-axial with said pilot burner tube and disposed within said chamber for flow of said mixture from a point upstream therefrom over the radially inner and outer annular sides of said annular channel means, said annular channel means having an open side facing downstream relative to said flow and having a diameter larger than the diameter of said pilot burner tube at its discharge end; and a plurality of linear channel members extending from said pilot burner tube to said annular channel means and being circumferentially-spaced about the axis of said annular channel means for flow of at least a portion of said mixture therebetween, each said linear channel member having an open side facing in the direction of the flow over said member and the channel of each linear channel member communicating at one end with said pilot burner tube and at its other end with the channel of said annular channel means.
2. In combustion apparatus having a combustion chamber and means for supplying a main combustible mixture to said chamber; the combination therewith of means for igniting said main combustible mixture; said igniting means comprising first annular channel means disposed within said chamber across the flow path of said main combustible mixture for flow of said main mixture from a point upstream therefrom over the radially inner and outer annular sides of said annular channel means, said annular channel means having an open side facing in a downstream direction relative to said flow; pilot burner means having means for providing its own combustion mixture and communicating with said annular channel means for causing a pilot flame to extend into the channel of said annular channel means; second annular channel means. disposed across said flow path co-axial with and downstream of said first annular channel means and having an annular open side facing in said downstream direction; and a plurality of linear channel members each having one end communicating with the channel of said first annular channel means and having its other end communicating with the channel of said second annular channel means, said linear channel members diverging from each other in said downstream direction and being circurnferentially-spaced about the axis of said annular channel means for flow of at least a portion of said main mixture therebetween, the channel of each linear channel member being open on its downstream side relative to .the adjacent main mixture flow between said members.
3. Apparatus as recited in claim 2 in which the divergence of said linear channel members is such that each linear channel member is inclined to the axis of said annular channel means by no more than approximately and in which at least the major portion of each annular channel means and each linear channel member has a V-shaped cross-section with its apex on its upstream side.
4. In combustion apparatus having a combustion chamber and means for supplying a main combustible mixture to said chamber; the combination therewith of means forigniting said main combustible mixture; said igniting means comprising a pilot burner disposed in said chamber and having means for providing its own combustible mixture; first annular channel means disposed within said chamber co-axial with and adjacent to the discharge end of said pilot burner and disposed across the flow path of said main combustible mixture for flow of said main mixture from a point upstream therefrom over. the radially inner and outer annular sides of said annular channel means, said annular channel means having an open side facing in a downstream direction relative to said flow and having a radius larger than that of the discharge end of said pilot burner; a first plurality of linear channel members extending from said pilot burner to said first annular channel means, the channel of each of said linear channel members communicating at one end with said pilot burner and at its other end with the channel of said annular channel means; second annular channel means co-axially disposed downstream of said first annular channel means, said second annular channel means having a larger radius than said first annular channel means and having an open side facing in said downstream direction; and a plurality of second linear channel members each having one end communicating with the channel of said first annular channel means and having its other end communicating with the channel of said second annular channel means, each of said plurality of linear channel members being circumferentially-spaced about the axis of said annular channel means for flow of said main combustible mixture between said members and the channel of each said linear channel member being open on its downstream side relative to the adjacent main combustible mixture flow between said second linear channel members.
5. Apparatus as recited in claim 4 in which said second annular channel means has an inner radius larger than the outer radius of said first annular channel means and. said second linear channel members diverge from each other in said downstream direction so that each second linear channel member is inclined to the axis of said annular channel means by no more than 10.
6. Apparatus as recited in claim 5 in which at least the major portion of each said annular channel means and each said linear channel member has a V-shaped crossection with its apex on its upstream side.
7. Apparatus as recited in claim 4 in which said second annular channel means has an inner radius larger than the outer radius of said first annular channel means and said second linear channel members diverge from each other in said downstream direction so that each second linear channel member is inclined to the axis of said annular channel means by approximately 4 to 7.
8. Apparatus as recited in claim 7 in which said pilot burner includes a burner tube having an open discharge end of reduced diameter with said open discharge end facing in said downstream direction and with the downstream end of said first annular channel means being disposed downstream of said burner tube discharge end.
9. In combustion apparatus having a combustion chamber and means for supplying a main combustible mixture to said chamber; the combination therewith of means for igniting said main combustible mixture; said igniting means comprising first annular channel means disposed within said chamber for flow of said main mixture from a point upstream therefrom over the radially inner and outer sides of said annular channel means, said annular channel means having an open side facing in a downstream direction relative to said flow; a plurality of circumferentially-spaced pilot burners interposed in said annular channel means, each pilot burner having means for providing its own combustible mixture and having a burner tube with the open end of said burner tube being directed in said downstream direction and with each burner tube having a pair of slots in its side wall providing communication between said tube and the adjacent portions of the channel of said annular channel means; second annular channel means co axially disposed downstream of said first annular channel means, said second annular channel means having a radius larger than said first annular channel means and having an open side facing downstream relative to said main mixture flow; and a plurality of linear channel members each having one end communicating with the channel of said first annular channel means and having its other end communicating with the channel of said second annularrchannel means, said ,plurality of linear channel members being circumferentially-spaced about the axis of said annular channel means for flow of at least-aportion of said main mixture between said members and each linear channel member having an open side facing in the direction of the adjacent main mixture fiow between said members.
10. Apparatus as recited in claim 9 in which the channel of each annular channel means and each linear channel member diverges toward its open side and each pilot burner tube has flame holder means extending thereacross inwardly of the open end of said tube and adjacent to the apex of the adjacent portions of the channel of said first annular channel means and in which said linear channel members diverge in said downstream direction such that each linear channel member is inclined to the axis of said annular channel means by no more than 10.
11. In a jet engine including a duct, a center body coaxially disposed within said duct and having a streamlined outer periphery, a combustion chamber within said duct downstream of said center body and means for supplying a combustible mixture of air and fuel to said combustion chamber through the annular path about said center body; the combination therewith of means for igniting said combustible mixture for combustion in said chamber; said igniting means comprising a pilot burner co-axially disposed within said streamlined center body, said pilot burner including a burner tube having an open discharge end in which the discharge passage of said burner tube includes the entire cross-sectional area of the space between the outer walls of said tube at said discharge end; means for supplying fuel and air to said pilot burner tube; and a plurality of circumferentially-spaced means extending radially outwardly from said tube across the flow path of said combustible mixture for flow of said mixture thereover from a point upstream therefrom, said lastmentioned means communicating with said pilot burner tube for spreading the pilot burner flame outwardly therefrom across said flow path.
12. In a jet engine including a duct, a center body coaxially disposed within said duct and having a streamlined outer periphery, a combustion chamber within said duct downstream of said center body, and means for supplying a combustible mixture of air and fuel to said combustion chamber through the annular path about said center body; the combination therewith of means for igniting said combustible mixture in said chamber; said igniting means comprising a pilot burner co-axially disposed within said center body and spaced from the surrounding wall of said center body to provide annular passage means therebetween, said pilot burner including a burner tube having an open discharge end disposed at the downstream end of said center body and in which the discharge passage of said burner tube includes the entire cross-sectional area of the space between the outer walls of said tube at said discharge end; means for supplying fuel and air into said center body to said pilot burner tube, a portion of said air flowing out through said annular passage means about the pilot burner for cooling said pilot burner; and a plurality of circumferentially-spaced channel means each having an open channel side facing in a downstream direction, said channel means extending radially outwardly from said tube across the flow path of said combustible mixture adjacent to the upstream end of said chamber for flow of said mixture over said channel means from a point upstream therefrom, one end of said channel means communicating with said pilot burner tube for spreading the pilot burner flame outwardly therefrom across said flow path.
13. In a jet engine including a duct, a center body coaxially disposed within said duct and having a streamlined outer periphery, a combustion chamber within said duct downstream of said center body, and means for supplying a combustible mixture of air and fuel to said com- 8 bustion chamber through the annular path within said duct about said center body; the combination therewith of means for igniting said combustible mixture in 'said chamber; said igniting means comprising a pilot burner having a pilot burner tube co-axially disposed withinsaid center body and spaced from the surrounding wall of said center body to provide annular passage means therebetween, said pilot burner tube having a discharge-end of reduced diameter disposed at the downstream end of said center body; means for supplying air into said center body to said pilot burner, a portion of said air flowing out through said annular passage means about the pilot burner tube'for cooling said tube; annular channel means having its open side directed in a downstream direction, said annular channel means being co-axially disposed and extending downstream of the discharge end of said pilot burner tube and having a radius larger than that of said discharge end; and a plurality of circumferentially-spaced linear channel members extending from said pilot burner tube to said annular channel means, the channel of each of said linear channel members communicating at one end with the pilot burner tube and at its other end with the channel of said annular channel means and the open channel side of each linear channel member facing in a downstream direction.
14. In a jet engine including a duct, a center body coaxially disposed within said duct and having a streamlined outer periphery, a combustion chamber within said duct downstream of said center body, and means for supplying a combustible mixture of air and fuel to said combustion chamber through the annular path within said duct about said center body; the combination therewith of means for igniting said combustible mixture in said chamber; said igniting means comprising a pilot'burner having a pilot burner tube co-axially disposed within said center body and spaced from the surrounding Wall of said center body to provide annular passage means therebetween, said pilot burner tube having a discharge end of reduced diameter disposed at the downstream end of said center body; means for supplying air into said center body to said pilot burner, a portion of said air flowing out through said annular passage means about the pilot burner tube for cooling said tube; first annular channel means having its open channel side directed in a downstream direction relative to the flow of said combustible mixture, said annular channel means being co-axial with and extending downstream of the discharge end of said pilot burner tube and having a radius larger than that of said discharge end; a first plurality of circumferentially-spaced linear channel members extending from said pilot burner tube to said annular channel means, the channel of each of said linear channel members communicating at one end with the pilot burner and at its other end with the channel of said annular channel means and the open channel side of each linear channel member facing in a downstream direction; a second plurality of circumferentially-spaced linear channel members each having its channel communicating with the channel of said first annular channel means said second linear channel members extending in a downstream direction from said first annular channel means and diverging from each other such that each second linear channel member is inclined to the axis of said pilot burner by approximately 4 to 7 with its open side facing inwardly; and second annular channel means coaxial with said first annular channel means and extending across the downstream ends of said second linear channel members with its channel communicating with the channel of each of said second linear channel members, said second annular channel means having its open side directed in said downstream direction.
15, In a jet engine including a duct, a center'body coaxially disposed within said duct and having a streamlined outer periphery, a combustion chamber downstream of said center body, and means for supplying a combustible mixture of air and fuel to said combustion chamber through the annular path about said center body; the combination therewith of means for igniting said combustible mixture for combustion in said chamber; said igniting means comprising a pilot burner co-axially disposed Within said streamlined center body, said pilot burner including a burner tube having an open discharge end of reduced diameter terminating at the downstream end of said center body; first annular channel means having its open side directed in a downstream direction, said annular channel means being co-axially disposed and extending downstream of the discharge end of said pilot burner tube and having a radius larger than that of the discharge end of the pilot burner tube; a first plurality of circumferentially-spaced linear channel members extending from said pilot burner tube to said annular channel means, the channel of each of said linear channel members communicating at one end with the pilot burner tube and at its other end with the channel of said annular channel means and the open channel side of each linear channel member facing in a downstream direction; a second plurality of circumferentially-spaced linear channel members each having its channel communicating at one end with the channel of said first annular channel means, said second linear channel members extending in a downstream direction from said first annular channel means and diverging from each other such that each second linear channel is inclined to the axis of said pilot burner by approximately 4 to 7 with its open side facing inwardly; and second annular channel means co-axial with said first annular channel means and extending across the downstream ends of said second linear channel members with its channel communicating with the channel of each of said second linear channel members, said second annular channel means having its open side directed in a downstream direction.
16. In a jet engine including a duct, a center body coaxially disposed within said duct, a combustion chamber downstream of said center body, and means for supplying a combustible mixture of air and fuel to said combustion chamber through the annular path about said center body; the combination therewith of means for igniting said combustible mixture for combustion in said chamber; said igniting means comprising a pilot burner co-axially disposed at the downstream end of said center body, said pilot burner including a burner tube; first annular channel means having its open side directed in a downstream direction, said annular channel means being co-axially disposed and extending downstream of the discharge end of said pilot burner tube and having a radius larger than that of the discharge end of the pilot burner tube; a first plurality of circumferentially-spaced linear channel members extending from said pilot burner tube to said annular channel means, the channel of each of said linear channel members communicating at one end with the pilot burner tube and at its other end with the channel of said annular channel means and the open channel side of each linear channel member facing in a downstream direction; a second plurality of circumferentially-spaced linear channel members each having its channel communicating at one end with the channel of said first annular channel means, said second linear channel members extending in a downstream direction from said first annular channel means and diverging from each other such that each second linear channel is inclined to the axis of said pilot burner by no more than approximately 10 with its open side facing inwardly; and second annular channel means co-axial with said first annular channel means and extendacross the downstream ends of said second linear channel members with its channel communicating with the channel of each of said second linear channel members, said second annular channel means having its open side directed in a downstream direction.
17. In a jet engine including a duct, a center body co-axially disposed within said duct, a combustion chamber within said duct downstream of said center body, and
means for supplying a combustible mixture of air and fuel to said combustion chamber through the annular path about said center body; the combination therewith of means for stabilizing combustion within said chamber; said stabilizing means comprising means providing a sheltered chamber co-axially disposed at the downstream end of said center body and having an open downstream end; annular channel means having its open channel side directed in a downstream direction relative to flow of said combustible mixture, said annular channel means 'being co-axially disposed downstream of said chamber and having a diameter larger than the diameter of the downstream end of said chamber; and a plurality of circumferentially-spaced linear channel members extending from said chamber to said annular channel means, each of said linear channel members having the open side of its channel facing in said downstream direction and having its channel communicating at one end with said chamber and its other end with the channel of said annular channel means.
18. In a jet engine including a duct, a center body coaxially disposed within said duct, a combustion chamber within said duct downstream of said center body, and means for supplying a combustible mixture of air and fuel to said combustion chamber through the annular path about said center body; the combination therewith of means for stabilizing combustion within said chamber; said stabilizing means comprising means providing a sheltered chamber co-axially disposed at the downstream end of said center body and having an open downstream end; first annular channel means having its open channel side directed in a downstream direction relative to flow of said combustible mixture, said annular channel means being co-axially disposed downstream of said chamber and having a diameter larger than the diameter of the downstream end of said chamber; a first plurality of circumferentially-spaced linear channel members extending from said chamber to said annular channel means, each of said linear channel members having the open side of its channel facing in said downstream direction and having its channel communicating at one end with said chamber and its other end with the channel of said annular channel means; second annular channel means having its open channel side directed in said downstream direction, said second annular channel means being co-axially disposed downstream of said first annular channel means and having a diameter larger than the diameter of said first annular channel means; and a second plurality of circumferentially-spaced linear channel members extending from said first to said second annular channel means, each of said second linear channel members having the open side of its channel facing in said downstream direction and having its channel communicating at one end with the channel of said first annular channel means and at its other end with the channel of said second annular channel means.
19. In a jet engine including a duct, a center body coaxially disposed within said duct, a combustion chamber within said duct downstream of said center body, and means for supplying a combustible mixture of air and fuel to said combustion chamber through the annular path about said center body; the combination therewith of means for stabilizing combustion within said chamber; said stabilizing means comprising means providing a sheltered chamberco-axially disposed at the downstream end of said center body and having an open downstream end; first annular channel means having its open channel side directed in a downstream direction relative to flow of said combustible mixture, said annular channel means being co-axially disposed downstream of said chamher and having a diameter larger than the diameter of the downstream end of said chamber; a first plurality of circumferentially-spaced linear channel members extending from said chamber to said annular channel means, each of said linear channel members having the open side of its channel facing .in said downstream direction and -havin1g its channel communicating at one end with said chamber andits other end with the channel of said annular channel means; second annular channel means having its open channel side directed in said downstream direction, said second annular channel means co-axial with and axially spaced from said first annular channel means and having a diameter larger than the diameter of said first annular channel means; and a second plurality of circumferentially-spaced linear channel members extending from said first to said second annular channel means, each of said second linear channel members having the open side of its channel facing in said downstream direction and having its channel communicating at one end with the channel of said first annular channel means and at its '12 other "end with the channel of saicl's'econdiannular channel means.
References Cited in the file of this patent UNITED STATES PATENTS Brzozowski Mar. 24, 1953
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US230212A US2872785A (en) | 1951-06-06 | 1951-06-06 | Jet engine burner apparatus having means for spreading the pilot flame |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US230212A US2872785A (en) | 1951-06-06 | 1951-06-06 | Jet engine burner apparatus having means for spreading the pilot flame |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| US2872785A true US2872785A (en) | 1959-02-10 |
Family
ID=22864337
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US230212A Expired - Lifetime US2872785A (en) | 1951-06-06 | 1951-06-06 | Jet engine burner apparatus having means for spreading the pilot flame |
Country Status (1)
| Country | Link |
|---|---|
| US (1) | US2872785A (en) |
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| US2937501A (en) * | 1955-07-13 | 1960-05-24 | Sud Aviation | Combustion devices for ram-jet engines |
| US2958196A (en) * | 1959-01-02 | 1960-11-01 | Gen Electric | Flame igniter for gas turbine combustor |
| US2964907A (en) * | 1957-11-15 | 1960-12-20 | Rolls Royce | Combustion stabilising device for combustion equipment |
| US2974488A (en) * | 1956-11-27 | 1961-03-14 | Snecma | Combustion devices for continuous-flow internal combustion machines |
| US2979900A (en) * | 1957-11-12 | 1961-04-18 | United Aircraft Corp | Ducted fan flameholder |
| US3002352A (en) * | 1957-11-12 | 1961-10-03 | United Aircraft Corp | Flameholder construction |
| US3046742A (en) * | 1959-01-05 | 1962-07-31 | Gen Motors Corp | Combustion apparatus |
| US3274776A (en) * | 1964-07-06 | 1966-09-27 | Nord Aviation | Combustion chambers of reaction propulsion units |
| US3292375A (en) * | 1963-03-29 | 1966-12-20 | Rolls Royce | Combustion equipment, e. g. for a gas turbine engine |
| US4562699A (en) * | 1961-10-23 | 1986-01-07 | Rolls-Royce Limited | Mixing chambers for continuous flow engines |
| US5099644A (en) * | 1990-04-04 | 1992-03-31 | General Electric Company | Lean staged combustion assembly |
| US20050198940A1 (en) * | 2004-03-10 | 2005-09-15 | Koshoffer John M. | Ablative afterburner |
| US7565804B1 (en) | 2006-06-29 | 2009-07-28 | General Electric Company | Flameholder fuel shield |
| US7581398B2 (en) | 2006-06-29 | 2009-09-01 | General Electric Company | Purged flameholder fuel shield |
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| US2552492A (en) * | 1948-06-07 | 1951-05-08 | Power Jets Res & Dev Ltd | Air ducting arrangement for combustion chambers |
| US2592110A (en) * | 1949-05-21 | 1952-04-08 | Curtiss Wright Corp | Orifice type flame holder construction |
| US2632300A (en) * | 1949-08-03 | 1953-03-24 | Thermal Res & Engineering Corp | Combustion stabilization means having igniter grill heated by pilotburner |
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2937501A (en) * | 1955-07-13 | 1960-05-24 | Sud Aviation | Combustion devices for ram-jet engines |
| US2974488A (en) * | 1956-11-27 | 1961-03-14 | Snecma | Combustion devices for continuous-flow internal combustion machines |
| US2979900A (en) * | 1957-11-12 | 1961-04-18 | United Aircraft Corp | Ducted fan flameholder |
| US3002352A (en) * | 1957-11-12 | 1961-10-03 | United Aircraft Corp | Flameholder construction |
| US2964907A (en) * | 1957-11-15 | 1960-12-20 | Rolls Royce | Combustion stabilising device for combustion equipment |
| US2935847A (en) * | 1957-11-18 | 1960-05-10 | United Aircraft Corp | Flow control means for use with flameholders and flamespreaders |
| US2958196A (en) * | 1959-01-02 | 1960-11-01 | Gen Electric | Flame igniter for gas turbine combustor |
| US3046742A (en) * | 1959-01-05 | 1962-07-31 | Gen Motors Corp | Combustion apparatus |
| US4562699A (en) * | 1961-10-23 | 1986-01-07 | Rolls-Royce Limited | Mixing chambers for continuous flow engines |
| US3292375A (en) * | 1963-03-29 | 1966-12-20 | Rolls Royce | Combustion equipment, e. g. for a gas turbine engine |
| US3274776A (en) * | 1964-07-06 | 1966-09-27 | Nord Aviation | Combustion chambers of reaction propulsion units |
| US5099644A (en) * | 1990-04-04 | 1992-03-31 | General Electric Company | Lean staged combustion assembly |
| US20050198940A1 (en) * | 2004-03-10 | 2005-09-15 | Koshoffer John M. | Ablative afterburner |
| US7251941B2 (en) | 2004-03-10 | 2007-08-07 | General Electric Company | Ablative afterburner |
| US7565804B1 (en) | 2006-06-29 | 2009-07-28 | General Electric Company | Flameholder fuel shield |
| US7581398B2 (en) | 2006-06-29 | 2009-09-01 | General Electric Company | Purged flameholder fuel shield |
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