US3800531A - Self-starting annular jet engine with plural burner and bypass duct - Google Patents

Abstract

An engine including a self-starting engine compressor unit comprising a burner duct defining a converging-diverging inlet at its forward end, a converging exhaust nozzle at its rear end, and a combustion chamber therebetween; a fuel injection device for injecting fuel under pressure axially through the throat of the inlet into the combustion chamber to draw air therewith into the chamber; and preheater means for heating the chamber to a predetermined temperature. The compressor unit may include a bypass duct encircling the burner duct with an inlet opening forward of the inlet to the burner duct and a converging exhaust opening rearward of the exhaust nozzle so that air will be drawn through the bypass duct by the jet pumping action of the exhaust gases from the burner duct in combination with the exhaust opening in the bypass duct. The fuel injection device may be equipped with pressure responsive means for transferring the point of injection from forward of the throat of the inlet of the burner duct to a point rearward of the throat and within the combustion chamber. The compressor unit may be embodied in a jet engine as a start stage with intermediate and final ram-jet type stages.

Description

United States Patent Sharpe SELF-STARTING ANNULAR JET ENGINE WITH PLURAL BURNER AND BYPASS DUCT Inventor: Thomas H. Sharpe, 502 Darr Ave.,

Belvedere, SC. 29841 Filed: June 4, 1973 Appl. No.: 366,332

Related US. Application Data [63] Continuation-in-part of Ser. No. 191,627, Oct. 22,

1971, Pat. No. 3,750,400.

[52] US. Cl 60/263, 60/39.49, 60/241, 60/269, 60/39.52, 60/39.36, 60/264 [51] Int. Cl......, F02k 3/10 [58] Field of Search 60/263, 203, 267, 264, 60/269, 39.52, 3949,3936, 241, 242, 247

[56] References Cited UNITED STATES PATENTS 2,663,142 12/1953 Wilson 60/263 2,721,444 10/1955 Johnson 60/264 2,705,396 4/1955 Boyce et al. 60/264 2,686,473 8/1954 Vogel 60/267 3,323,304 6/1967 Llobet et al. 60/39.49 2,616,258 11/1952 Mock 60/39.36 3,138,919 6/1964 Deutsch.... 60/267 3,517,510 6/1970 Melenric 60/39.49

Primary Examiner-Carlton R. Croyle Assistant ExaminerWarren Olsen [57] ABSTRACT An engine including a self-starting engine compressor unit comprising a burner duct defining a convergingdiverging inlet at its forward end, a converging exhaust nozzle at its rear end, and a combustion chamber therebetween; a fuel injection device for injecting fuel under pressure axially through the throat of the inlet into the combustion chamber to draw air therewith into the chamber; and preheater means for heating the chamber to a predetermined temperature. The compressor unit may include a bypass duct encircling the burner duct with an inlet opening forward of the inlet to the burner duct and a converging exhaust opening rearward of the exhaust nozzle so that air will be drawn through the bypass duct by the jetpumping action of the exhaust gases from the burner duct in combination with the exhaust opening in the bypass duct. The fuel injection device may be equipped with pressure responsive means for transferring the point of injection from forward of the throat of the inlet of the burner duct to a point rearward of the throat and within the combustion chamber. The compressor unit may be embodied in a jet engine as a start stage with intermediate and final ram-jet type stages.

PMENTEUAPR 21914 SHEET U30F11 PAIENTEDAPR 21914 SNEET 0 [1F 11 PAIENTED APR 21974 SHEET '05 HF 11 \Qm i 1 w mm Ev mmnmn I n I \1\ W mm fin mg m 3v 7 v 5% WW mm min H H mm f mwfim m a q m Sm whn/ 9 z mum Ev a n "3 \V ow \m mum Mm kw NR QR MNM mm Nu v m mm mm m Sn 7 mQNI .1: E hmwv MN 3% QQm PMENIEU APR- 21974 SHEET 08 0F 11 PAIENIED APR 2 ISM SHEET 09 0F 11 PATENIEBAPR 2 I974 SHEET "19 0F 11 SELF-STARTING ANNULAR JET ENGINE WITH PLURAL BURNER AND BYPASS DUCT CROSS-REFERENCE TO RELATED APPLICATIONS This application is a continuation-in-part of my copending application Ser. No. 191,627, filed Oct. 22, 1971, entitled Engine now US. Pat. No. 3,750,400.

BACKGROUND OF THE INVENTION Because jet engines must be capable of operating at low plane speeds. currently used engines require a compressor stage for supplying air under pressure to the burner section thereof and a turbine stage driven by the exhaust gases of the burner section to rotate the compressor stage. This requirement for rotating machinery has increased the weigh of the engine as well as limited the maximum temperatures within the engine. Also, the high rotational speed of the rotating parts has required critical dynamic balancing of the parts and extensive maintenance to keep the engine operating properly.

SUMMARY OF THE INVENTION These and other problems associated with the prior art are overcome by the invention disclosed herein by providing a means for supplying air to the burner section of the engine which requires no rotating parts in the compressor itself or in the engine after the burner section. The invention maintains operation while the engine is stationery or moving at slow speeds. Because of the lack of moving parts, the temperatures within the engine can be raised to produce a more effective operation.

The apparatus of the invention includes a compressor start stage comprising a burner duct including a burner section and an exhaust nozzle, an inlet duct at that end of the burner duct opposite the exhaust nozzle, a fuel injection device for injecting fuel under pressure axially through the reduced diameter throat of the inlet duct and into the burner duct to draw air into the burner section through the inlet duct, and a pre-heater for heating the burner section. The exhaust from the start stage may be injected through the inlet duct of at least one intermediate stage to achieve a jet pump action therethrough and pressurize the burner section of the intermediate stage. Fuel injected into the intermediate stage supports combustion therein and the exhaust therefrom may be injected into the main engine stage to produce combustion and a final thrust.

These and other features and advantages of the in vention will become more fully understood upon consideration of the following specification and accompanying drawings wherein like characters of reference designate corresponding parts throughout the several views and in which:

FIG. 1 is an enlarged longitudinal cross-sectional view of one embodiment of the invention;

FIG. 2 is a front view of the start stage of FIG. 7;

FIG. 3 is an enlarged cross-sectional view of the fuel injection head of the start stage of FIG. 1;

FIG. 4 is a longitudinal cross-sectional view showing the embodiment of FIG. 1 installed in an engine;

FIG. 5 is a transverse cross-sectional view taken along line 5--5 in FIG. 4;

FIG. 6A is a longitudinal cross-sectional view of a portion of another embodiment of the invention;

FIG. 6B is a continuation of FIG. 6A showing the rest of the embodiment;

FIG. 7 is a cross-sectional view taken along line 77 in FIG. 6A;

FIG. 8A is a longitudinal cross-sectional view of a portion of a second embodiment of the invention;

FIG. 8B is a continuation of FIG. 8A;

FIG. 9 is an inlet end view of the embodiment of FIG. 8A;

FIG. 10 is an enlarged cross-sectional view of one unit of the start stage of FIG. 8A;

FIG. 11 is an inlet end view of FIG. 10;

FIG. 12 is a longitudinal cross-sectional view of still another embodiment of the invention;

FIG. 13 is a front view of the embodiment of FIG. 12;

FIG. 14 is a cross-sectional view taken along line l414 in FIG. 13; and,

FIG. 15 is an enlarged portion of FIG. 12.

These figures and the following detailed description disclose specific embodiments thereof, however, it is to be understood that the inventive concept is not limited thereto since it may be incorporated in other forms.

DETAILED DESCRIPTION OF ILLUSTRATIVE EMBODIMENTS Referring now to FIGS. 1-3, the first embodiment of the invention includes a self-starting jet pump compressor unit 10. This unit is capable of sustaining combustion at zero forward speed and to produce an increased pressure at its exhaust or pump end.

The unit 10 includes a generally cylindrical burner duct 11 with an annular duct wall 12 forming a substantially constant diameter burner chamber 14 intermediate its ends, a converging-diverging inlet 15 with a reduced diameter throat 16 smaller than the diameter of the burner camber 14 at the front end of duct 16, and a converging exhaust nozzle 18 at the rear end of duct 11 with a throat 19 of a diameter smaller than that of chamber 14.

A fuel injection assembly 20 is positioned just forwardly of inlet 15 for injecting fuel through inlet 15 and into chamber 14 axially along the centerline CL of duct 11. Referring to FIG. 3, the assembly 20 includes a cylindrical stationary housing 21 concentrically mounted forwardly of inlet 15 by struts 22 attached to duct wall 12. Housing 21 defines an axially extending cylindrical passage 24 concentric about centerline CL of duct 11. An inwardly extending annular retaining lip 25 extends around and projects into passage 24 at its rear end and a similar annular retaining lip 26 extends around and projects into passage 24 at its forward end. An annular abutment 28 extends around passage 24 at its central portion.

An intermediate extension tube 30 is slidably received in passage 24 between lip 25 and abutment 28. Tube 30 includes a cylindrical body 31 of a constant diameter just sufficient to slidably pass through the opening of lip 25 and an annular projecting flange 32 at the forward end thereof just sufficient to slidably move along passage 24 but be retained between abutment 28 and lip 25. A compression coil spring 34 is received about the body 31 of tube 30 between flange 32 and lip 25 to constantly urge tube 30 toward abutment 28. A central support passageway 35 axially extends through tube with an annular inwardly extending lip 36 at its rear end and a similar lip 38 at its forward end.

A fuel nozzle tube 40 is slidably received in passageway 35, and includes a main body portion 41 of constant diameter just sufficient to pass through the opening of lip 36 with an annular outwardly projecting flange 42 at its forward end sufficient to slidably move in passageway and be retained between lips 36 and 38. A compression coil spring 44 is received about the main body portion 41 between lip 36 and flange 42 to constantly urge tube forwardly against lip 38 in passageway 35. An axially extending fuel passage 45 is defined through nozzle tube 40 which communicates with passage 24 in housing 21 at its forward end and into the burner duct 11 at its rear end.

An inlet spike is slidably mounted about housing 21 and in passage 24 forwardly of abutment 28 and includes a central shaft 51 of a constant diameter just sufficient to slidably pass through the opening defined by lip 26, a disc 52 on the rear end of shaft 51 slidably received in the forward portion of passage 24 and retained between abutment 28 and lip 26, and a conical spike head 54 on the forward end of shaft 51 and extending back over the housing 21. A compression coil spring 55 is received around shaft 51 between disc 52 and lip 26 to constantly urge spike 50 rearwardly toward abutment 28.

A fuel line 56 communicates with passage 24 through abutment 28 and with a pressurized fuel supply source (not shown). In the fully retracted position, the rear end of the intermediate extension tube 30 is substantially flush with the rear end of housing 21 and the discharge end of the nozzle tube 40 is positioned axially within the inlet 15 forward of its throat 19 so that fuel discharged from fuel passage 45 will be injected axially through throat 19 into the burner chamber 14. The spike head 54 is fully retracted rearwardly over housing 21 and about struts 22. The operation of the assembly 20 will be explained in more detail hereinafter.

A preheater assembly 60 is mounted in the burner chamber 14 for preheating same prior to injection of fuel therein in order to start unit 10. Assembly 60 may be any of a number of available preheating means and is shown as a heating coil 61 carried within appropriate recesses 62 around the inside of duct wall 12 at the burner chamber. This allows substantially unrestricted passage of the combustion medium through chamber 14. Coil 16 is connected to an appropriate power source (not shown) to heat same as will be explained.

Fuel line 56 is connected to the pressurized fuel supply source through a heat transfer section 64 located in duct wall 12 at the exhaust nozzle 18 and includes a series of passages 65 in duct wall 12. The fuel passes through the passages 65 on its way to the fuel injection assembly 20 to be heated while at the same time cooling the duct wall 12.

A by-pass duct is concentrically located about the burner duct 11 and defines a central opening 71 therethrough into which the duct 11 is positioned on struts 72. The duct wall 74 defines a diverging inlet 75 just forward of the inlet 15 of duct 11 and a convergingdiverging outlet 76 just rearwardly of exhaust nozzle 18. As combustion takes place within burner chamber 14, the discharging exhaust gases from the exhaust nozzle 18 pass through the reduced diameter throat 78 of outlet 76 to cause air to be drawn into inlet 75 by a jet pump effect.

In order to retain the combustion within the burner chamber 14, conventional flame holders 79 are concentrically mounted in burner chamber 41 rearwardly of the throat 16 of inlet 15. The flame holders 79 are carried by mounting bars 80 attached'to duct wall 12 of the duct 11. Igniter plugs 81 may be provided to start combustion.

A feedback bleed tube may be fitted to the duct 11 and provided with an inlet 91 at the converging section of exhaust nozzle 18. A forwardly facing scoop 92 is provided within duct wall 12 to direct a small portion of the high velocity exhaust gases into a pressure reservoir 94 in tube 90. The trapped gases pressurized the tube 90 and travel forwardly along tube 90 to a manifold 95 in struts 22 to pressurize same. The gases then pass from manifold 95 back into inlet 15 through nozzles 96 to force more air into chamber 14.

OPERATION In operation, power is first supplied to the preheater assembly 60 to heat the air within the burner chamber 14 to the approximate ignition temperature of the fuel. This also heats the fuel within the heat transfer section 64 so that it will be substantially completely vaporized when it leaves the passage 45 in fuel nozzle tube 40. When the appropriate temperature is reached, the fuel supply injects the fuel through the passage 24 and out of the fuel passage 45 through the throat 16 of inlet 15 and into the heated air in the burner chamber 14. The igniter plugs 81 are powered in conventional manner so that as the incoming high velocity fuel stream mixes with the air combustion takes place. At the same time, the incoming fuel stream draws more air into burner chamber 14 to pressurize same and supply more air to support combustion. The preheater assembly 60 and igniter plugs 81 are then de-powered and the combustion is self-sustaining. It is to be understood that the preheater assembly 60 may be integrated with the heat transfer section 64 or that the fuel may be preheated before it reaches the section 64 and this heat used to heat chamber 14 without or in combination with the assembly 60.

As the exhaust gases exit through the exhaust nozzle 18 of duct 11, they pass through the throat 78 of outlet 76 to create a suction at the inlet 75 to draw additional air into unit 10 to further pressurize the burner chamber 14.

Since the unit 10 is designed for use as a compressor stage in ajet engine as will be described, the fuel injection assembly 20 is provided with means for moving the point of injection of the fuel from forward of throat 16 to a position behind the throat in burner chamber 14 when the pressure within the burner chamber 14 due to the ram effect from the velocity of the unit is sufficient to support combustion. This is provided by increasing the pressure of the fuel being supplied in response to ram pressure to a point where the intermediate extension tube 30 and fuel nozzle tube 40 are fully extended against the force of springs 34 and 44 as seen by dashed lines in FIG. 1. This converts unit 10 into a ram jet. At the same time, the spike 50 is moved forwardly as shown by dashed lines in FIG. 1 to open up the inlet 15 and allow more air to enter the unit 10. When the incoming air to inlet 15 becomes supersonic, spike head 54 of inlet spike 50 also generates a shock wave ahead of the inlet 15 to increase the static pressure.

The fuel nozzle tube 50 may also be equipped with multiple nozzles, each directing a stream of vaporized fuel substantially axially through the throat 16 of inlet 15 in lieu of the single fuel passage 45. This allows more fuel to be injected into the burner chamber 14 while at the same time generating enough jet pumping effect to force the necessary additional air into chamber 14 to support combustion and provide the necessary mixing of fuel and air.

ENGINE INSTALLATION As seen in FIGS. 4 and 5, units are installed in an engine 100 to provide sufficient pressure within the engine to operate same even when the engine is stationary. Engine 100 has a main duct tube 101 having an annular side wall 102. Wall 102 defines a diverging inlet opening 104 with a main burner chamber 105 of increasing diameter thereafter and terminating in a converging outlet 106. A tapered burner can 108 is concentrically located within chamber 105 by struts 109 between the side wall 102 of tube 101 and the can wall 110 of burner can 108. The rear end of can wall 110 forms a converging exhaust nozzle 111 which discharges through the larger diameter outlet 106. Burner can 108 is provided with dircumferentially extending slots 112 with forwardly facing air scoops 114 along the rear endges of slots 112 as will be explained.

The smaller forwardly facing end of burner can 108 joins with the rear end of a compressor unit 10 so that the exhaust gases and air discharged through the outlet 76 of unit 10 moves axially rearwardly along the centerline CL-A of the engine 100 and burner can 108. An annular fuel manifold 115 is positioned in burner can 108 behind the outlet 76 of unit 10 and is provided with rearwardly facing nozzles 116 of conventional design for spraying the fuel into can 108. Flame holders 117 may be provided in cna 108 to retain the flame.

A plurality of units 10 are positioned in the annular passage 120 between the burner can 108 and side wall 102 of duct tube 101 near the rear end of the can 108. The units 10 are equally spaced circumferentially about can 108 so that the exhaust gases and air discharged from each of their outlets 76 are directed through the converging outlet 106 of duct tube 101 to draw air moving along the annular passage 120 into the burner can 108.

In operation, the units 10 are ignited as set forth hereinabove to draw air into the inlet opening 104. The unit 10 in front of the burner can 108 discharge the airexhaust gas mixture therefrom axially along the burner can 108 while the remaining units 10 discharge the airexhaust gas mixture through the outlet 106 to draw air along the annular passage 120. The forwardly facing air scoops 114 direct a portion of the air from passage 120 into the interior of can 108 and the jet pumping action of the discharging air-exhaust gas mixture also draws additional air into the burner can 108.

After the units 10 are operating, fuel is supplied to manifold 115 and discharge rearwardly by nozzles 116 where it is mixed with the air and exhaust gas mixture within burner can 108 and ignited by the heat of the exhaust gases from the forward unit 10 and combustion is sustained for the engine 100 to produce thrust.

SECOND ENGINE INSTALLATION Referring to FIGS. 6A-7, the unit 10 is incorporated in an engine 200 of the axial flow type. The unit 10 has the by-pass duct removed therefrom and is equipped with a variable throat exhaust nozzle assembly 201. Assembly 201 includes a plurality of arcuate vanes 202 slidably positioned about the nozzle 18 of duct 11 and selectively positioned by a plurality of fluid cylinders 204. An appropriate guide 205 is provided to cause the vanes 202 to pass along the duct wall 12 to selectively throttle the exhaust gases being discharged from the burner chamber 14 as will be explained.

The unit 10is concentrically mounted in the forward end of a cowling tube 206 described below by a pair of mounting struts 208. Mounted rearwardly of the unit 10 concentrically in tube 206 is an intermediate stage 210 carried by struts 208.

The intermediate stage 210 is aligned with the discharging exhaust gases from unit 10 and receives additional air from the jet pump arrangement at the forward end thereof to support combustion therein. Stage 210 includes a main tube 211 with an annular tube wall 212 concentrically located about the centerline CL-B of engine 200. Tube 211 defines a converging diverging inlet 214 at its forward end spaced rearwardly of the vanes 202 on unit 10. The diameterof the throat 215 of inlet 214 is larger than the maximum opening provided by vanes 202.

Rearwardly of inlet 214 wall 212 defines a combustion chamber 216 and the rear end of tube 210 defines a converging exhaust opening 218. A fuel manifold 219 is positioned around the outside of tube wall 212 at the forward end of combustion chamber 216 with a plurality of fuel nozzles 220 of conventional design protruding through the tube wall 212 into the combustion chamber 216. An inlet spike 221 may be mounted in the forward end of combustion chamber 216 to act as a diffuser section within chamber 216 especially at supersonic air-exhaust gas mixture flow rates through the throat 215 of inlet 214. Flame holders 222 may be provided aft of the fuel nozzles 220 to maintain the flame within combustion chamber 216.

A throttling assembly 230 complimentary to the assembly 201 of unit 10 is provided forward of inlet 214. Assembly 230 includes a plurality of movable vanes 231 around inlet 214 to define a converging-diverging opening. Vanes 231 are carried by the forward end of tube wall 212 and selectively positioned by a plurality of fluid cylinders 234 so as to vary the annular opening between vanes 202 and the converging walls 235 of vanes 231. This serves to vary the amount of air pumped through the inlet 214 of stage 210 by the jet pumping action of the exhaust from unit 10.

A variable throat exhaust nozzle assembly 240 is provided about the exhaust opening 218 of tube 211. The nozzleassembly 240 is similar in construction to the nozzle assembly 201 with a plurality of arcuate vanes 241 slidably mounted in guide 242 and positioned by cylinders 244 so as to vary the discharge opening of stage 210 and throttle the exhaust therefrom.

A generally semi-circular cowling 250 is provided about the throttling assembly 230 with its open mouth 251 extending over the rear end of unit 10 to provide an air metering passage 252 into the inlet 214 of stage 210.

A main thrust stage 260 is mounted within cowling tube 206 rearwardly of intermediate stage 210 by struts 261 and aligned with the discharging exhaust gases from unit 10. Additional air is supplied thereto by the jet pump arrangement at the forward end thereof to support combustion therein.

The main thrust stage 260 is similar in construction to the intermediate stage 210 except larger with a main thrust tube 262 having a converging-diverging inlet 264, combustion chamber 265, and a convergingdiverging exhaust outlet 266. A fuel manifold 268 encircles the outside of tube 262 and has a plurality of conventional fuel nozzles 269 projecting into combustion chamber 265. A plurality of flame holder rings 270 are positioned in chamber 265 and an inlet spike 271 is mounted on struts 272 in the forward end of combustion chamber 265 to act as a diffuser section in chamber 265, especially at supersonic air-exhaust gas mixture flow rates through inlet 264.

A throttling assembly 274 similar to assembly 230 and complimentary to the exhaust nozzle assembly 240 at the rear end of intermediate stage 210 is provided on the forward end of tube 262. The assembly 274 cooperates with assembly 240 similarly to the co-operation between assembly 230 and assembly 201 to selectively throttle the amount of air drawn through the inlet 264 of the main thrust stage 260 by the jet pumping action of the exhaust gases discharged by intermediate stage 210. Assembly 274 includes a plurality of movable vanes 275 around inlet 264 to form a convergingdiverging opening and slidably mounted on guide 276. A plurality of fluid cylinders 278 control the position of the vanes 275.

A generally semi-circular cowling 280 is provided about the throttling assembly 274 similarly to cowling 250 of intermediate stage 210. The forwardly facing open mouth 281 of cowling 280 extends over the rear end of stage 210 to provide an air metering passage 282 into the inlet 264 of the main thrust stage 260. The cowling 280 includes an cylindrical annular outer wall 284 which extends rearwardly from mouth 281 to join with the thrust tube 262 at its combustion chamber. This provides an annular by-pass duct 285 around the main thrust stage 260 as will be explained.

A cooling ring assembly 286 is positioned around the reduced diameter portion of tube 262 at the exhaust outlet 266 to direct a portion of the air from the by-pass duct 285 along the outer surface of tube 262 and cool same.

The cowling tube 206 defines the outside of the engine and mounts the compressor unit 10, intermediate stage 210 and main thrust stage 260 in its central cavity 290. Tube 206 has an annular cylindrical side wall 291 which projects forwardly of the unit 10 to provide a diverging inlet duct 292 forwardly of unit 10 and terminates substantially in the same plane as the exhause outlet 266 of the main thrust stage 260.

A flap-type augmentated exhaust nozzle assembly 294 is mounted on the rear end of cowling tube 206. Assembly 294 includes a plurality of flaps 295 hinged to the tube 206 and positioned by fluid cylinders 296 in known manner. The varying of the position of flaps 295 serves to control the amount of by-pass air drawn through duct 285 by the jet pumping action of the exhaust from the main thrust stage 260.

OPERATION OF SECOND ENGINE INSTALLATION In operation, the compressor unit 10 is ignited as set forth hereinabove. Its exhaust gases are injected axially through the inlet 214 of intermediate stage 210 which creates a jet pumping action to draw additional air into stage 210 through the annular metering opening defined between vanes 202 and 231 and also to draw additional air into the inlet 15 of unit 10. The jet pumping action of unit 10 pressurizes the burner chamber 216 of stage 210.

When fuel is sprayed into the chamber 216 by nozzles 220, ignition takes place because of the heat from the exhaust gases of unit 10 and operation of the intermediate stage 210 starts. The discharging exhaust gases from stage 210 are injected through the inlet 264 of the main thrust stage 260. This causes air to be drawn into the stage 260 through the annular opening between vanes 241 and 275 to pressurize the burner chamber 265 thereof. When fuel is supplied via nozzle 269 to chamber 65, ignition takes place from the heat of the exhaust gases of stage 210. The exhaust gases from stage 260 discharging through the nozzle assembly 294 causes additional air to be drawn into the engine via the inlet duct 292 to further pressurize the engine.

Because control systems for controlling the amount of fuel injected into the engine 200 as well as the position of the assemblies 201, 230, 240, 274 and 294 are available, these controls are not described. It will be seen that the jet pumping action of each stage is summed, sufficient operating pressure is maintained within the engine.

THIRD ENGINE INSTALLATION Referring now to FIGS. 8A-l0, the invention is embodied in engine 300 having a compressor stage 301, an intermediate stage 302, and a main thrust stage 304.

Engine 300 includes a main cowling tube 305 which mounts the various engine stages therein. The compressor stage 301 includes a plurality of compressor units 310 positioned within the forward portion of tube 305 and equally spaced concentrically about the centerline CL-3 of engine 300. The compressor units 310 are mounted between an inner tube ring 311 and an outer tube ring 312 concentrically located with respect to each other and to the centerline CL-3 to form a compressor annulus 314 therebetween. An outwardly projecting bend 315 is formed in inner ring 311 just inwardly of its forward end and, in conjunction with a complementary inwardly projecting bend 316 formed in outer ring 312, forms an annular throat 318 between the rings 311 and 312. The rear end of inner ring 311 is angled outwardly to form a nozzle flange 316 and in conjuction with the inwardly angled complementary flange 320 of outer ring 312, forms an annular exhaust nozzle 321 between rings 311 and 312. The rings 311 and 312 are arranged so that the throat 318 is axially aligned with exhaust nozzle 321.

Each unit 310 as best seen in FIGS. 10 and 11 includes a primary fuel metering assembly 325 positioned in the converging portion of annulus 314 forwardly of the throat 318 thereof. Assembly 325 has a cylindrical body 326 with a forwardly facing projection 328 extending toward the inlet of annulus 314 and a rearwardly facing low pressure fuel nozzle 329 for injecting fuel axially through the throat 318 as will be explained. Unit 310 is mounted by struts 330 connected to rings 311 and 312. Positioned rearwardly of throat 318 in alignment with assembly 325 is a ring manifold 331 having a plurality of rearwardly facing fuel nozzles 332 in the forward end of the annular combustion chamber 334 defined by rings 311 and 312.

Each nozzle 329 and ring manifold 331 is supplied fuel from a distribution manifold 335 extending around 'the outside of the ring 312 within bend 316. Each nozzle 329 is connected to manifold 335 through a low pressure bypass valve 336 that restricts fuel flow to the nozzle inversely to the inlet pressure at annulus 314 to allow the fuel to flow to nozzle 329 at lower inlet pressure and decrease the flow as inlet pressure increases until the fuel flow is cut off at nozzle 329 when a predetermined inlet pressure is reached. Each ring manifold 331 is connected to manifold 335 through a high pressure bypass valve 338 which allows fuel to flow to ring manifold 331 when the inlet pressure at annulus 314 reaches the predetermined valve at which the fuel flow is cut off to nozzle 329. The fuel is supplied to the manifold 335 from the fuel source through a heat transfer tube 337 in the combustion chamber 334 to preheat the fuel prior to injection through nozzle 329 and nozzles 332. Flame holders 340 may be positioned in the combustion chamber 334 behind each fuel metering assembly 325 and ring manifold 331 to retain the flame in combustion chamber 334.

A heating coil 345 is placed in the combustion chamber 334 rearwardly of flame holders 340 behind each fuel metering assembly 325 so that preheating as described for unit 10 can take place. This insures starting of each unit 310.

An air bleed tube 346 similar to tube 90 for unit 10 connects the rear end of combustion chamber 334 with a chamber 348 in struts 330. Each tube 346 has a forwardly facing scoop 349 projecting into chamber 334 to direct the gases into a reservoir 350 in tube 346. A plurality of rearwardly facing ports 351 in struts 330 inject the gases from chamber 348 through throat 318 to assist in pressurizing combustion chamber 334.

An inner tubular section 355 is positioned inside of ring 311 and concentrically therewith by struts 356 to define an inner bypass 359 between section 355 and ring 311. An outer tubular section 358 is positioned outside of ring312 and concentrically therewith to define an outer bypass 360 between section 358 and ring 312. An outwardly angled flange 361 is provided at the forward end of section 355 and, in conjunction with an inwardly angled flange 362 on the forward end of section 358, defines a diverging inlet 364 forward of the inlet of the compressor stage 301. The rearmost end of tubular section 355 is provided with an outwardly angled flange 365, which, in conjunction with an inwardly angled flange 366, forms an annular exhaust nozzle 368 for the first power unit 370 of intermediate stage 302.

Just rearwardly of the exhaust nozzle 321 of compressor stage 301, the inner tubular section 355 is provided with an outwardly projecting bend 371, which, in conjunction with a complementary inwardly projecting bend 372 in the outer tubular section 358, forms the inlet 374 of power unit 370 with throat 375 having a slightly larger opening than that of the exhaust nozzle 321 of compressor stage 301 and axially aligned therewith. This forms an annular combustion chamber 376 between inlet 374 and exhaust nozzle 368. A ring 378 covers the depression of bend 371 and a ring 379 covers the depression of bend 372 to provide a smooth inner surface along section 355 and a smooth outer surface along section 358.

An annular cone shaped burner shroud liner 380 is positioned in combustion chamber 376. The forwardly facing converging portions of the side walls 377 of liner 380 are shaped to define an annular convergingdiverging inlet 383 as best seen in FIG. 8A with an annular throat 387. A plurality of fuel nozzles 381 are provided which are connected to the fuel source through heat transfer coil 373 in combustion chamber 376 just forwardly of exhaust nozzle 368. The nozzles 381 are circumferentially spaced about the inlet 383 so that the fuel discharged rearwardly therefrom forwardly of the throat 387 will pass axially through the throat 387 to pump air therewith into the linear 380. The liner 380 serves as a flame holder to retain the combustion flame within chamber 376.

The second power unit 385 of intermediate stage 302 includes an inner tubular section 386 and an outer tubular section 388. The forward ends of sections 386 and 388 project just forwardly of exhaust nozzle 368 of the first power unit and are provided with outwardly and inwardly directed projections 389 and 390 respectively to form an annular converging-diverging inlet 391 with throat 392 axially aligned with an exhaust opening in nozzle 368. Inlet passages 394 and 395 are defined between projection 389 and flange 365 and between projection 390 and flange 366. The rearmost ends of tubular sections 386 and 388 are provided respectively with an outwardly flaring flange 396 and an inwardly flaring flange 398 to form a converging exhaust nozzle 399.

An annular combustion chamber 400 is defined between inlet 391 and exhaust nozzle 399. An annular cone shaped burner shroud liner 401 is positioned in combustion chamber 400 as best seen in FIG. 8A. The forwardly facing converging portions of the side walls 403 of liner 401 are shaped to define an annular converging-diverging inlet 407 with an annular throat 413. A plurality of fuel nozzles 402 are circumferentially spaced about the inlet 407 so that fuel discharged rearwardly therefrom forwardly of the throat 413 will pass axially through the throat 413 to pump air therewith into the liner 380. The nozzles 402 are connected to the fuel source through a heat transfer coil 417 positioned in combustion chamber 400 just forwardly of exhaust nozzle 399.

The main thrust stage 304 is positioned rearwardly of the second power unit 385 of intermediate stage 302 and includes an inner tubular section 4.04 projecting within the flange 396 of unit 385 and on outer tubular section 405 projecting around flange 398 of unit 385. The forward end of section 404 has an inwardly extending projection 406 to form an annular convergingdiverging inlet 408 with an inwardly extending projection 409 on the forward end of tubular section 405. An annular inner inlet duct 410 to stage 304 is defined between flange 396 of unit 385 and projection 406 and an annular outer inlet duct 411 is defined between flange 398 of unit 385 and projection 409.

The rearmost end of tubular section 404 has an outwardly flaring flange 412 which forms a diverging exhaust nozzle 414 with an inwardly flaring flange 415 at the rearmost end of tubular section 405. This defines an annular combustion chamber 416 between inlet 408 and exhaust nozzle 414.

A compound burner can assembly 418 is positioned in combustion chamber 416. Can assembly 418 includes an annular cone shaped inner shroud liner 419 and outer shroud liner 420. The forwardly facing converging portions of the side walls 423 of inner liner 419 are shaped to define an annular converging-diverging inlet 427 with an annular throat 431. The forwardly facing converging portions of the side walls 432 of outer liner 420 are shaped to define an annular converging-diverging inlet 434 with an annular throat 435. A plurality of fuel nozzles 436 are circumferentially spaced about both inlets 427 and 434 so that fuel dsscharged rearwardly therefrom forwardly of the throat 431 and 435 will pass axially through the throat 431 and 435 to pump air therewith into the liners 419 and 420. The nozzles 436 are connected to the fuel source through a heat transfer coil 438 positioned in combustion chamber 416 just forwardly of exhaust nozzle 414.

The main cowling tube 305 defines a diverging inlet duct 425 forwardly of compressor stage 301 and a converging exhaust opening 426 rearwardly of the exhaust nozzle 414 of the main thrust stage 304. Since the cow]- ing tube 305 is larger in diameter than any of stages 301, 302 or 304, a bypass duct 428 is provided along the length of engine 300 outside of stages 301, 302 and 304. A cone member 429 is positioned in the exhaust opening 426 with its forwrdly facing tapered end 430 projecting within flange 412. The converging portion of tube 305 at exhaust opening 426 defines a bypass air inlet duct 431 with flange 415 and member 429 defines an inner air inlet duct 432 with flange 412.

OPERATION OF THIRD ENGINE INSTALLATION Engine 300 is started similarly to engine 200. First, the heating coils 345 are supplied with electricity to heat same. This also heats the air within the annular combustion chamber 334 in the vicinity of each unit 310 to a temperature sufficient to ignite the fuel as with unit 10. It is also to be understood that coils 345 may extend completely around the rings 311 and 312 to achieve the same result.

When the desired temperature is reached, fuel under pressure is supplied to the low pressure fuel nozzle 329 of each unit 310. The inlet pressure is sufficiently low to not open valves 338 so that no fuel is supplied to chamber 334 from the nozzles 332 of ring manifold 331. The fuel is ejected from the low pressure nozzles 329 in small streams at high velocity axially through the throat 318 of annulus 314 and into combustion chamber 334. This causes air to be drawn into chamber 334 with the fuel through throat 318 by the jet pumping influence of the fuel. When the fuel reaches the heated air in chamber 334, it ignites to starts combustion. The additional fuel and air entering chamber 334 sustains the combustion once it has started and the heat of combustion maintains the proper operating temperature in the chamber 334 thus allowing the coils 345 to be shut off.

The exiting exhaust gases from the exhaust nozzle 321 pump additional air into the combustion chamber 376 of the first power unit 370 via the inlet 364, bypasses 359 and 360, and throat 375 of inlet 374 because of the jet pumping action of the gases in combination with the throat 375 of unit 370. This also draws additional air into the throat 318 of the compressor stage 301. A portion of the exhaust gases is trapped by the scoops 349 of the units 310 to pressurize the bleed tubes 346 and force these gases rearwardly out of ports 351 and struts 330. The jet pumping action of the exiting gases from the ports 35] forces additional air into the combustion chamber 334 to pressurize same and support combustion.

The exhaust gases from the compressor stage 301 passing into the chamber 376 of the first power unit 370 heats same to fuel ignition temperature whereupon fuel is sprayed from nozzles 381 into chamber 376 to start combustion within this unit. The exiting exhaust gases from the nozzle 368 of power unit 370 creates a jet pump effect as it passes through the throat 392 of the second power unit 385 to draw air into the combustion chamber 400 from the central passage 357 of the tubular section 355 and from the bypass duct 428 through the inlet passages 394 and 395 to support combustion. This also draws additional air into the front of engine 300 to further pressurize the inlet to units 310. Once combustion chamber 400 is pressurized, the fuel is sprayed therein by fuel nozzles 402 to start combustion.

The exhaust gases from the second power unit 385 are injected axially through the inlet 408 of the main thrust stage 304 to pressurize same from the jet pump action drawing air through inlet ducts 410 and 411 from the central passage 387 of inner tubular section 386 and from the bypass duct 428. Once the combustion chamber 416 is pressurized, fuel is sprayed therein from fuel nozzles 421 to start combustion.

As the exhaust gases from the main thrust stage 304 passes through the exhaust opening 426 in the cowling tube 305, they exert a jet pumping action drawing air through the bypass duct 428 and the central passage 403 of the tubular section 404 thus drawing more air into the inlet duct 425 and further pressurizing the stages 301, 302 and 304.

When the velocity of the engine 300 with respect to the ambient air is sufficient to sustain combustion pressure from the ram effect, control means (not shown) causes the valves 336 to shut off fuel flow to nozzles 329 and to open valves 339 to supply fuel to nozzles 332 since the jet pumping action of units 310 is no longer needed.

FOURTH ENGINE INSTALLATION Referring now to FIG. 12, the fourth embodiment of the invention is an engine 500 which has a jet pumping action directed from the center of the engine outwardly. Engine 500 includes a compressor stage-501, an intermediate stage 502 and a main thrust 504 concentrically mounted about the centerline CL-S of the main cowling tube 505. I

The compressor unit 501 has an open duct 510 centrally located in cowling tube 505 at the forward end thereof. Duct 510 has a tubular wall 51 l defining a cylindrical inlet passage 512 and with an annular projection 514 at the rear end of passage 512 defining a throat 515 and a combustion chamber 516 therebehind. Combustion chamber 516 is terminated by the wall 51 1 converging to form an exhaust nozzle 518 with an elongated cylindrical exhaust duct 519 extending through the intermediate stage 502'seen in FIG. 15.

A fuel injection assembly 520 similar to assembly 20 of unit is positioned in inlet passage 512 so that the fuel nozzle 521, in its forward retracted position, is positioned ahead of throat 515 so that the fuel is sprayed axially therefrom through throat 515 into combustion chamber 516 and draws air into the chamber 516 similarly to that described hereinabove. The nozzle 521 may be made to extend through throat 515 similar to the assembly for unit 10. The incoming fuel to assembly 520 is preheated in a heat transfer coil 517.

A preheater coil 522 is positioned in combustion chamber 516 similarly to coil 61 in unit 10. This heats the air in chamber 516 to start combustion and also preheats the fuel.

The intermediate stage 502 includes an open ended duct 530 with a tubular wall 531 positioned concentrically about duct 510 of stage 501. Wall 531 has an inwardly projecting annular section 532 which, together with an outwardly projecting annular section on duct 510, forms a converging-diverging annular inlet passage 534 to combustion chamber 538. Chamber 538 is provided with a compound annular burner canassembly 539 with annular cone shaped inner and outer burner shroud liners 540 and 541 respectively. The forwardly facing converging portions of side walls 542 of inner liner 540 are shaped to define an annular converging-diverging inlet 544 with an annular throat 545. The forwardly facing converging portions of the side walls 546 of outer liner 541 are shaped to define an annular converging-diverging inlet 548 with an annular throat 549. A plurality of fuel nozzles 550 are circumferentially spaced about both inlets 544 and 548 so that fuel discharged rearwardly therefrom forwardly of the throats 545 and 549 will pass axially through the throats 545 and 549 and pump air therewith into the liners 540 and 541. The nozzles 550 are connected to the fuel source through a heat transfer coil 551 positioned in the combustion chamber 538 to preheat same.

The duct wall 531 has an inwardly tapering section 552 behind the combustion chamber 538 to form a converging exhaust nozzle 554 with a cylindrical exhaust duct 555 extending through the main thrust stage 504 and concentrically about the duct 519 of stage 501. Duct 519 terminates within duct 555 in FIG. 12.

The main thrust stage 504 includes a duct tube 560 with a tubular wall 561 extending forwardly tothe inlet ends of the stages 501 and 502 and concentrically about the duct tube 530 of stage 502. Wall 561 has an inwardly projecting annular section 562 which, in combination with an outwardly projecting annular section 564 on wall 531, forms a converging-diverging annular inlet passage 565 about stage 502 to the combustion chamber 566. This chamber, like chamber 538 of stage 502, is provided with a compound burner can assembly 568 with annular cone shaped inner and outer burner shroud liners 570 and 571 respectively. The forwardly facing converging portions of side walls 572 of inner linear 570 are shaped to define an annular convergingdiverging inlet 574 with an annular throat 575. The forward facing converging portions of the side walls 576 of outer liner 571 are shaped to define an annular converging-diverging inlet 578 with an annular throat 579. A plurality of fuel nozzles 580 are circumferentially spaced about both inlets 574 and 578 so that fuel discharged rearwardly therefrom forwardly of the throats 575 and579 will pass axially through the throats 575 and 579 and pump air therewith into the liners 570 and 571. The nozzles 580 are connected to the fuel source through a heat transfer coil 581 positioned in the combustion chamber 566 to preheat same.

Duct wall 561 tapers inwardly after chamber 566 to form a converging exhaust nozzle 582 and a cylindrical exhaust duct 584 concentric about duct 555. It will be noted that duct 555 terminates within duct 584.

The cowling tube 505 has an outwardly flaring inlet wall section 585 extending from the vicinity of the forward end of combustion chamber 566 of stage 504 forward of the inlets to stages 501, 502 and 504 to define a diverginginlet 586. A cylindrical wall section 588 encircles the combustion chamber 566 of start 504 and an inwardly tapered wall section 589 joins with the rear end of section 588 to extend past the end of duct 584 of stage 504' and form a converging discharge 590.

The intermediate stage 502 and the main thrust stage 504 are provided with regenerative compression units 600 and 601 respectively The unit 600 includes an annular passage 602 which is connected to an annular opening 604 in the duct wall 531 in the vicinity of the rear of combustion chamber 538. A forwardly facing intake 605 is provided at opening 604 that projects within duct 530 to direct a portion of the escaping exhaust gases from the combustion chamber 538 through opening 604 into the passage 602 and forwardly therealong.

A plurality of radially extending rear injection struts 610 are provided between the duct wall-51l and the duct wall 531. The struts 610 are equallyspaced circumferentially about the wall 511 and lie in a transverse plane through the engine just forwardly of the inlet passage 534. A bore 611 as seen in FIG. 14 longitudinally extends through each strut 610 and communicates with the passage 602 through opening 612 seen in FIG. 15 in duct wall 531. A plurality of rearwardly directed nozzle passages 614 connect with bore 611 to inject the exhaust gases in passage 602 rearwardly through inlet passage 534. A plurality of side nozzle passages 615 also communicate with bore 611 to inject the exhaust gasses in passage 602 rearwardly toward inlet passage 534 and outwardly from strut 610.

A plurality of radially extending front injection struts 620 are provided between the duct wall 511 and the duct wall 531. The struts 620 are equally spaced circumferentially about the wall 511 and lie in a transverse plane through the engine a prescribed distance a forwardly of rear struts 610. The struts 620 are staggered with respect to struts 610 as best seen in FIG. 13. A bore 621 as seen in FIG. 14 longitudinally extends through each strut 620 and communicates with the passage 602 through opening 622 seen in FIG. 15 in duct wall 531. A plurality of rearwardly directed nozzle passages 624 connect with bore 611 to inject the exhaust gases in passage 602 rearwardly toward inlet passage 534 and outwardly from strut 620.

The discharging exhaust gases from the side nozzle passages 615 in the rear struts 610 and from the side nozzle passages 625 in the front struts 620 overlap so as to set up a barrier layer around the inlet passage 534 to prevent the exhaust gases in the combustion chamber 538 from backing out through the inlet passage 534 during combustion. It will also be noted that the exhaust gases discharged from struts 610 and 620 will force enough fresh air through the inlet passage 534 to support combustion, especially in combination with the jet pumping action of the discharging exhaust gases from the compressor unit50l.

The unit 601 as seen in FIG. 12 includes an annular passage 630 which is connected to an annular opening 631 in the duct wall 561 in the-vicinity of the rear of combustion chamber 566. A forwardly facing intake 632 is provided'at opening 631 that projects within duct 560 to direct a portion of the escaping exhaust gases from the combustion chamber 566 through opening 631 into thepassage 630 between the wall 630 and duct wall 561 and forwardly therealong.

A plurality of radially extending rear injection struts 635 are provided between the duct wall 531 and the duct wall 561. The struts 635 are equally spaced circumferentially about the wall 531 andlie in a transverse plane through the engine just forwardly of the inlet passage 565. A plurality of radially extending front injection struts 641 are provided between the duct wall 531 and the duct wall 561.'The struts 641 are equally spaced circumferentially about the wall 531 and lie in a transverse plane through the engine a prescribed distance b forwardly of rear struts 635. The struts 641 are staggered with respect to struts 635 as best seen in FIG. 13. The struts 635 and 641 have a construction similar to those in FIG. 14 with a central bore communicating with passage 630, rearwardly directed nozzle passages and side nozzle passages.

The discharging exhaust gases from the struts 635 and 641 perform similarly to the struts 610 and 620 so as to set up a barrier layer around the inlet passage 565 to prevent the exhaust gases in the combustion chamber 566 from backing out through the inlet passage 565 during combustion. It will also be noted that the exhaust gases discharged from struts 635 and 641 will force enough fresh air through the inlet passage 565 to support combustion, especially in combination with the jet pumping action of the discharging exhaust gases from the intermediate stage 502.

It is to be understood that the intakes 605 and 632 to the regenerative compression units 600 and 601 may be located at different points within combustion chambers 538 and 565. Further, the location and number of struts 610, 620, 635 and 641 may be varied. The operating fuel pressure may be provided by pumps 650 driven by the heated fuel passing from the coils 517, 551 and 581 as seen in FIG. 12.

This engine is started similarly to the previous embodiments. The primary jet pumping action is performed by the escaping exhaust gases from the stages 50], 502 and 504 and air is drawn into the engine starting from the inside and moving outwardly. Additionally, a portion of the exhaust gases from the intermediate stage 502 is fed back through its inlet passage 534 by the regenerative compression unit 600 to force additional air through passage 534. Also, a portion of the exhaust gases from the main thrust stage 504 is fed back through its inlet passage 565 by the regenerative compression unit 601 to force additional air through passage 565.

It is to be understood that the fuel injection assembly may be interchanged with the assembly 335 without departing from the scope of the inventive concept. Moreover, it isto be understood that any of the engines may be equipped with bypass air throttling means as illustrated for engine 200 and that those engines nothaving air bleed tubes in the compressor stage may be so equipped. A plurality of bleed tubes may be used in lieu of the tube for unit 10.

While specific embodiments of the invention have been disclosed herein, it is to be understood that full use of modifications, substitutions, and equivalents may be made without departing from the scope of the inventive concept.

I claim:

1. A self-starting engine including:

a tubular housing defining a primary diverging inlet at its forward end, an outwardly flaring bypass chamber intermediate its ends, and a primary converging exhaust nozzle at its rear end;

tubular outwardly flaring burner can mounted within said bypass chamber concentrically therewith and defining an injection opening at its forward end, a primary combustion chamber and a converging exhaust opening at its rear end so as to form a bypass duct between said can and-said housing, said burner can including scoop means projecting outwardly into said bypass duct to direct air passing through said bypass duct into said primary combustion chamber of said cam; fuel nozzle means for spraying fuel into said primary combustion chamber of said can; and,

a pluralityof compressor units, each of said units comprising:

a burner duct including a compressor combustion chamber and a compressor exhaust nozzle;

a converging-diverging compressor inlet at that end of said compressor combustion chamber opposite said exhaust nozzle and defining a reduced diameter compressor throat;

a fuel injection device for injecting fuel under pressure axially through said throat of said compressor inlet and into said compressor combustion chamber to draw air into said burner duct through said compressor inlet; and,

preheater means for heating said compressor combustion chamber to a predetermined temperature,

one of said compressor units arranged to discharge its exhaust gases axially intosaid burner can through said injection opening andthe other of said plurality of compressor units mounted circumferentially about said burner can within said bypass duct forward of said primary exhaust nozzle of said housing.

2. The engine of claim 1 wherein each of said fuel injection devices includes-an injection nozzle having a discharge end, said nozzle having a first position so that its discharge end is located forwardly of said compressor throat and a second position so that its discharge end is located within said compressor combustion stage,'an iintermediate stage and a main thrust stage,

said compressor stage comprising:

a burner duct including an inner ring and an outer ring concentric with said inner ring, said inner

Claims (10)

1. A self-starting engine including: a tubular housing defining a primary diverging inlet at its forward end, an outwardly flaring bypass chamber intermediate its ends, and a primary converging exhaust nozzle at its rear end; a tubular outwardly flaring burner can mounted within said bypass chamber concentrically therewith and defining an injection opening at its forward end, a primary combustion chamber and a converging exhaust opening at its rear end so as to form a bypass duct between said can and said housing, said burner can including scoop means projecting outwardly into said bypass duct to direct air passing through said bypass duct into said primary combustion chamber of said cam; fuel nozzle means for spraying fuel into said primary combustion chamber of said can; and, a plurality of compressor units, each of said units comprising: a burner duct including a compressor combustion chamber and a compressor exhaust nozzle; a converging-diverging compressor inlet at that end of said compressor combustion chamber opposite said exhaust nozzle and defining a reduced diameter compressor throat; a fuel injection device for injecting fuel under pressure axially through said throat of said compressor inlet and into said compressor combustion chamber to draw air into said burner duct through said compressor inlet; and, preheater means for heating said compressor combustion chamber to a predetermined temperature, one of said compressor units arranged to discharge its exhaust gases axially into said burner can through said injection opening and the other of said plurality of compressor units mounted circumferentially about said burner can within said bypass duct forward of said primary exhaust nozzle of said housing.

2. The engine of claim 1 wherein each of said fuel injection devices includes an injection nozzle having a discharge end, said nozzle having a first position so that its discharge end is located forwardly of said compressor throat and a second position so that its discharge end is located within said compressor combustion chamber rearwardly of said compressor throat.

3. The engine of claim 1 wherein burner can includes a side wall, said side wall defining an opening therethrough immediately forward of each of said scoop means for the passage of the air deflected by said scoop means into said primary combustion chamber.

4. A self-starting engine including a compressor stage, an iintermediate stage and a main thrust stage, said compressor stage comprising: a burner duct including an inner ring and an outer ring concentric with said inner ring, said inner and outer rings defining an annular compressor converging-diverging inlet having a reduced diameter throat, an annular compressor combustion chamber rearwardly of said inlet and an annular compressor exhaust nozzle rearwardly of said combustion chamber; a fuel injection device including a plurality of primary injection nozzles circumferentially spaced about and forward of said compressor throat, a plurality of secondary sets of injection nozzles circumferentially spaced about the forward end of said compressor combustion chamber rearwardly of said throat, one secondary set of nozzles axially aligned with each of said primary nozzles, and pressure responsive fuel valve means connecting said primary and secondary sets of nozzles for controlling the flow of fuel to said nozzles; and, preheater means for heating said compressor combustion chamber to a predetermined temperature including a plurality of heating coils, one of said coils being axially with each of said primary nozzles, said intermediate stage comprising a first power unit and a second power unit, said first power unit including: a first inner tubular section and a first outer tubular section concentrically arranged with respect to each other and with said engine unit, said first inner and outer sections defining there-between a first diverging inlet forward of said compressor stage, inner and outer passages about said engine unit, a first reduced diameter throat rearwardly of said exhaust nozzle of said compressor stage, a first annular combustion chamber rearwardly of said first throat, and a first converging exhaust nozzle at the rear end thereof; and first burner assembly mounted within said first combustion chamber between said first inner and outer sections, said burner assembly including a first annular diverging shroud liner and a plurality of first fuel nozzles for injecting fuel within said liner; and said second power unit including: a second inner tubular section and a second outer tubular section concentrically arranged with respect to each other and with said first power unit, said second inner and outer tubular sections defining therebetween a second converging-diverging inlet at their forward ends axially aligned with said first exhaust nozzle of said first power unit for receiving the exhaust gases therefrom, a second annular combustion chamber, and second converging exhaust nozzle at their rear ends; and, a second burner assembly mounted within said second combustion chamber between said second inner and outer sections, said second burner assembly including a second annular diverging shroud liner and a plurality of second fuel nozzles for injecting fuel within said second liner; said main thrust stage receiving the exhaust gases from said intermediate stage and including: a main inner tubular section and a main outer tubular section concentrically arranged with respect to each other and to said second inner and outer tubular sections of said second power unit, said main inner and outer sections defining therebetween a main coverging-diverging inlet at their forward ends axially aligned with said second exhaust nozzle of said second power unit for receiving the exhaust gases therefrom, a main annular combustion chamber, and a main converging exhaust nozzle at their rear ends; and, a main burner assembly mounted within said main combustion chamber between said main inner and outer tubular sections including a main compound annular shroud liner and a plurality of main fuel nozzles for injecting fuel within said main shroud liner; and, said engine further including: thrust a main cowling tube mounting said compressor stage, said intermediate stage and said main thrust stage concentrically therein and defining a base inlet forward of said compressor stage; an annular bypass duct around the outside of said compressor stage, said intermediate stage and said main thrust stage; and a base converging exhaust opening rearwardly of said main thrus stage, said first power unit and said second power unit defining a first inner space between said first exhaust nozzle of said first power unit and said second inlet of said second power unit communicating with the opening in said first inner tubular section and a first outer space communicating with said bypass duct to draw air into said second power unit; and said second power unit and said main thrust stage defining a second inner space between said second exhaust nozzle of said second power unit and said main inlet of said main thrust stage communicating with the opening in said second inner tubular section and a second outer space communicating with said bypass duct to draw air into said main thrust stage.

5. The engine of claim 4 wherein said fuel injection device further includes a fuel line connected to said fuel valve means, said fuel valve means selectively transferring the fuel flowing through said fuel line from said primary to said secondary nOzzles.

6. The engine of claim 5 wherein said first and second shroud liners and said main compound shroud liner each define a converging-diverging liner inlet with a liner throat and wherein said first, second and main fuel nozzles are constructed and arranged to respectively discharge fuel forwardly of and axially through said liner throats.

7. A self-starting engine comprising: a compressor stage including: a compressor burner duct comprising a compressor combustion chamber and a compressor exhaust tube, a converging-diverging compressor inlet at that end of said compressor combustion chamber opposite said exhaust nozzle and defining a reduced diameter compressor throat, a fuel injection device for injecting fuel under pressure axially through said throat of said compressor inlet and into said compressor combustion chamber to draw air into said burner duct through said compressor inlet comprising an injection nozzle having a discharge end, said nozzle having a first position so that its discharge end is located forwardly of said compressor throat and a second position so that its discharge end is located within said compressor combustion chamber rearwardly of said compressor throat, and, preheater means for heating said compressor combustion chamber to a predetermined temperature; an intermediate stage including: an intermediate annular burner duct concentrically located about said compressor burner duct defining an annular converging-diverging intermediate inlet, an intermediate annular combustion chamber and an intermediate exhaust tube, and, intermediate fuel injection means for injecting fuel within said intermediate combustion chamber; and, a main thrust stage including: a main annular burner duct concentrically located about said intermediate burner duct defining an annular converging-diverging main inlet, a main annular combustion chamber and a main exhaust tube, and, main fuel injection means for injecting fuel within said main combustion chamber; said compressor exhaust duct terminating within said intermediate exhaust duct and said intermediate exhaust duct terminating within said main exhaust duct so that the exhaust gases from said compressor exhaust duct will cause air to be drawn into said intermediate combustion chamber through said main inlet by jet pumping action.

8. The engine of claim 7 further including regenerative compressor means for injecting a prescribed amount of the exhaust gases in said engine reareardly through said intermediate and said main inlets.

9. The engine of claim 8 wherein said regenerative compressor means includes a first unit for injecting a prescribed amount of the exhaust gases in said intermediate combustion chamber rearwardly through said intermediate inlet and a second unit for injecting a prescribed amount of the exhaust gases in said main combustion chamber rearwardly through said main inlet.

10. The engine of claim 9 wherein said first unit comprises: a first plurality of injectors positioned within said intermediate inlet forward of the throat of said inlet, said first injectoss circumferentially spaced about said inlet in a first transverse plane, each of said first injectors injecting exhaust gases rearwardly therefrom and laterally thereof, a second plurality of injectoss positioned wtthin said intermediate inlet forward of said first injectors, said second injectors circumferentially spaced about said inlet in a second transverse plane and staggered with respect to said first injectors, each of said second injectors injecting exhaust gases rearwardly therefrom and laterally thereof and, a first return duct connected to said first and second injectors at one end and said intermediate combustion chamber at the other end for supplying exhaust gases from said intermediate combustion chamber to said injectors; and, wherein said second unit comprises: a third plurality of injectors positioned within said main inlet forward of the throat of said inlet, said third injectors circumferentially spaced about said inlet in a third transverse plane, each of said third injectors injecting exhaust gases rearwardly therefrom and laterally thereof, a fourth plurality of injectors positioned within said main inlet forward of said third injectors, said fourth injector circumferentially spaced about said inlet in a fourth transverse plane and staggered with respect to said third injectors, each of said fourth injectors injecting exhaust gases rearwardly therefrom and laterally thereof and, a second return duct connected to said third and fourth injectors at one end and said main combustion chamber at the other end for supplying exhaust gases from said main combustion chamber to said injectors.

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