TW201738457A - Air turbine rocket engine and operating method thereof - Google Patents

Abstract

An air turbine rocket engine includes a combustion chamber, a mixing chamber, a turbine, a rotary shaft, a compressor, and a nozzle. The combustion chamber is used to provide a fuel-rich hot gas. The combustion chamber has a rear exhaust opening for discharge the fuel-rich hot gas. The mixing chamber is used for an air flow thereinto. The turbine is disposed in the mixing chamber and aligned with the rear exhaust opening. The turbine is used for driving the fuel-rich hot gas flow into the mixing chamber and mixed with the air to form a mixed fuel gas. The rotary shaft includes a front end connected to the turbine, and a rear end opposite to the front end. The compressor is disposed in the mixing chamber and connected to the rear end of the rotary shaft for stirring and pressing the mixed fuel gas. The nozzle is disposed in a rear end of the mixing chamber for discharge a temperature gas which produced by combustion of the mixed fuel gas.

Description

Air turbine rocket engine and its operation method

The present invention relates to a jet engine, and more particularly to an air turbine rocket engine having high mixing efficiency and a method of operating the same.

The existing air turbine rocket engine works on the principle that the rocket draws in air from the atmosphere and pressurizes it to provide compressed air into the combustion chamber during the ascent. Subsequently, fuel is injected into the combustion chamber to be mixed and burned with compressed air to generate high temperature gas. The high temperature gas will drive the turbine to operate to drive the compressor to rotate. Finally, the high temperature gas is discharged through the nozzle to generate thrust.

Since the fuel in the combustion chamber and the compressed air are only mixed through the turbine, it is easy to cause the fuel and the compressed air to be insufficiently mixed to affect the combustion efficiency.

Accordingly, it is an object of the present invention to provide an air turbine rocket engine capable of sufficiently mixing an oil-rich fuel with air to increase the mixing efficiency of the mixed oil and gas so that the mixed oil and gas can be nearly completely burned to generate high temperature gas. Thereby, high combustion efficiency and high thrust effect can be achieved.

Thus, the air turbine rocket engine of the present invention comprises a combustion chamber, a mixing chamber, a turbine, a rotating shaft, a compressor, and a nozzle.

The combustion chamber is configured to provide an oil-rich hot gas, the combustion chamber has a rear exhaust port for discharging the rich oil hot gas; the mixing chamber is configured to supply an air; the turbine is disposed in the mixing chamber and aligned with the rear row a gas port, the turbine is configured to drive the rich oil hot gas to the mixing chamber and mix with the air to form a mixed oil and gas; the rotating shaft comprises a front end connected to the turbine, and a rear end opposite to the front end; a compressor is disposed in the mixing chamber and connected to the rear end of the rotating shaft, the compressor is used for agitating and pressurizing the mixed oil and gas; a nozzle is disposed at a rear end of the mixing chamber for discharging the mixed oil and gas after combustion High temperature gas.

The air turbine rocket engine further includes a casing forming the combustion chamber and the mixing chamber, the casing forming an intake flow passage communicating with the mixing chamber, the intake flow passage being used for guiding This air flows into the mixing chamber.

The air turbine rocket engine further includes a valve device disposed on the casing for controlling circulation and blocking of the intake runner.

The valve device includes a cover plate for blocking the intake air flow passage, and a driving component connected to the cover plate, the driving component is configured to drive the cover plate to open the air flow passage that is not closed The position, and a closed position that closes the intake runner.

The air turbine rocket engine further includes a afterburning device disposed in the mixing chamber and located at a rear side of the compressor, the afterburning device including a flame stabilizer, and an oxidant injection for injecting an oxidant into the mixing chamber Device.

The air turbine rocket engine further includes a control device electrically connected to the driving component and the oxidant injector, wherein the control device is configured to control the driving component to drive the cover plate to move between the open position and the closed position. The control device is configured to control the oxidant injector to act to inject the oxidant, the air turbine rocket engine can operate in a low altitude propulsion mode, and operate in a rocket propulsion mode, the control device controls the low altitude propulsion mode a driving element drives the cover plate in the open position, the control device controls the oxidant injector to be closed, and when the rocket propulsion mode operates, the control device controls the driving component to drive the cover plate to move to the closed position, the control device controls The oxidant injector is turned on to inject the oxidant.

The control device is disposed in the casing and includes a controller, and an altimeter electrically connected to the controller, the controller is electrically connected to the oxidant injector and the driving component respectively, and the controller has a predetermined preset a flight altitude value for measuring a flight altitude of the air turbine rocket engine and transmitting the measured flight height value to the controller to enable the controller to receive the flight altitude value and the The predetermined flight height value is compared, and when the flight height value received by the controller is the same as the predetermined flight height value, the controller controls the driving component to drive the cover plate to move to the closed position and control the oxidant injection The device is turned on to inject the oxidant.

The afterburner further includes an igniter.

The air turbine rocket engine further includes an oil-rich gas generator for supplying an oil-rich gas into the combustion chamber, and the oil-rich gas is preheated by the combustion chamber to form the oil-rich hot gas.

Another object of the present invention is to provide an air turbine rocket engine operation method capable of sufficiently mixing an oil-rich fuel with air to increase the mixing efficiency of the mixed oil and gas, so that the mixed oil and gas can be almost completely burned to generate high temperature. Gas, by which, can achieve high combustion efficiency and produce high thrust.

Thus, the method of operation of the air turbine rocket engine of the present invention comprises the following steps:

(A) providing an oil-rich hot gas through a combustion chamber;

(B) driving the rich oil hot gas to a mixing chamber through a turbine, mixing the rich oil hot air with a air flowing into the mixing chamber to form a mixed oil and gas;

(C) agitating and pressurizing the mixed oil and gas through a compressor connected to the rear side of the turbine; and

(D) discharging the high-temperature gas generated by burning the mixed oil and gas through a nozzle.

In the step (B), the air flows into the mixing chamber via an intake passage communicating with the mixing chamber, and the air turbine rocket engine is operated when the air turbine rocket engine operates in a low altitude propulsion mode. A control device controls a cover plate in an open position in which the intake flow path is not closed.

When the control device controls to move the cover plate to a closed position that closes the intake flow passage, the control device simultaneously controls an oxidant injector located on the rear side of the compressor to be opened to inject an oxidant into the mixing chamber. The air turbine rocket engine is switched from the low altitude propulsion mode to a rocket propulsion mode operation.

The control device automatically controls the movement of the cover to the closed position and opens the oxidant injector based on the actual flying height of the air turbine rocket engine.

The control device includes a controller and an altimeter electrically connected to the controller. The controller is preset with a predetermined flying height value, and the altimeter is used to measure the flying height of the air turbine rocket engine and measure a flight altitude value is transmitted to the controller to enable the controller to compare the received flight altitude value with the predetermined flight altitude value, when the controller receives the flight altitude value and the predetermined When the flying height values are the same, the controller automatically controls the cover to move to the closed position and opens the oxidant injector.

The invention has the advantages that the turbine is aligned with the rear exhaust port of the combustion chamber, and the compressor is disposed on the rear side of the turbine, so that the turbine can mix the oil-rich hot gas with the air flowing into the mixing chamber for the first time. Subsequently, the compressor can perform a second mixing of the mixed oil and gas, thereby enabling the oil and gas in the mixed oil and gas to be sufficiently mixed to increase the mixing efficiency of the oil and gas. When the mixed oil and gas flows to the rear of the afterburning device, the mixed oil and gas can be almost completely burned to generate high-temperature gas, thereby achieving high combustion efficiency and enabling the air turbine rocket engine to have a high thrust effect in the low-altitude propulsion mode.

Before the present invention is described in detail, it should be noted that in the following description, similar elements are denoted by the same reference numerals.

1 and 2 are a first embodiment of an air turbine rocket engine according to the present invention. The air turbine rocket engine 1 is exemplified by a main engine of a rocket, which is suitable for use in, for example, a satellite or a spacecraft. The use of the cargo to outer space. The air turbine rocket engine 1 includes a casing 11, an oil-rich gas generator 12, a support frame 13, a rotating shaft 14, a turbine 15, a compressor 16, a afterburner 17, and a nozzle 18.

The casing 11 includes a front end 111 and a rear end 112 opposite to the front end 111. The casing 11 is formed with a combustion chamber 113 at a middle position, a mixing chamber 114 adjacent to the rear end 112, and two chambers 113. An intake passage 115 that communicates with the mixing chamber 114 on the left and right sides. The combustion chamber 113 has a rear exhaust port 116. Each of the intake runners 115 is configured to direct air from an external environment into the mixing chamber 114.

The rich oil generator 12 is disposed in the casing 11 adjacent to the front end 111. The rich oil generator 12 includes a fuel storage cylinder 121 on the front side of the combustion chamber 113, and an oxidant storage cylinder 122 on the front side of the fuel storage cylinder 121. . The fuel storage cylinder 121 is used to store fuel and is connected to the combustion chamber 113 through a delivery pipe 123 for storing the oxidant and is connected to the delivery pipe 123 through a delivery pipe 124. The fuel outputted by the conveying pipe 123 is first mixed with the oxidant outputted from the conveying pipe 124 to form an oil-rich gas, and then sent to the combustion chamber 113. The rich oil gas is burned and preheated in the combustion chamber 113 to form a gas. The oil-rich hot gas, rich oil hot gas can exit the combustion chamber 113 via the rear exhaust port 116.

The support frame 13 is disposed in the mixing chamber 114 and fixedly coupled to the inner wall surface of the peripheral wall 117 of the casing 11. The support frame 13 includes a plurality of front guide vanes 131 arranged in a ring shape, and a plurality of rings. The rear guide vanes 132 are spaced apart from each other, and the rear guide vanes 132 are spaced apart from the rear side of the front guide vanes 131. The rotating shaft 14 rotatably pivotally supports a plurality of bearings (not shown) of the support frame 13. The rotating shaft 14 includes a front end 141 and a rear end 142 opposite to the front end 141.

The turbine 15 of the present embodiment is exemplified by a centrifugal turbine. The turbine 15 is disposed in the mixing chamber 114 and aligned with the rear exhaust port 116 of the combustion chamber 113. The turbine 15 is fixedly coupled to the front end 141 of the rotating shaft 14. The rich oil hot gas is discharged to the turbine 15 through the rear exhaust port 116 of the combustion chamber 113 and then drives the turbine 15 to rotate. During the rotation of the turbine 15, the rich oil hot gas is caused to flow into the mixing chamber 114, so that the rich oil and the hot gas The air flowing into the mixing chamber 114 by each of the intake passages 115 is mixed to form a mixed oil and gas.

The compressor 16 is disposed in the mixing chamber 114 and fixedly coupled to the rear end 142 of the rotating shaft 14, and the compressor 16 is located between the front guide vane 131 and the rear guide vane 132 and on the rear side of the turbine 15. During the rotation of the turbine 15, the compressor 16 is driven to rotate through the rotating shaft 14. When the compressor 16 rotates, the mixed oil and gas is stirred to further increase the mixing efficiency, and at the same time, the mixed oil and gas is compressed.

The afterburning device 17 is disposed in the mixing chamber 114 and fixedly coupled to the inner wall surface of the peripheral wall 117 of the casing 11, and the afterburning device 17 is located on the rear side of the compressor 16 and the rear guide vane 132. The afterburner 17 includes a flame stabilizer 171 and an oxidant injector 172 for injecting an oxidant into the mixing chamber 114.

The nozzle 18 is disposed at the rear end 112 of the casing 11. The nozzle 18 is formed with a spray passage 181 communicating with the rear end of the mixing chamber 114. The spray passage 181 is configured to discharge the high-temperature gas generated after the combustion of the mixed oil and gas, thereby generating thrust.

Referring to Figures 2 and 3, the air turbine rocket engine 1 (shown in Figure 1) further includes a valve device 19 and a control device 20. The valve device 19 is disposed in the casing 11 for controlling the circulation and blocking of the two intake runners 115. The valve device 19 includes two cover plates 191 and two drive members 192 respectively connected to the two cover plates 191. Each of the cover plates 191 is configured to be closed to an air inlet 118 corresponding to the intake air flow path 115. Each of the driving elements 192 is disposed in the casing 11 for driving the corresponding cover plate 191 to move between an open position (as shown in FIG. 2) and a closed position (shown in FIG. 6). When each cover plate 191 is in the open position, each cover plate 191 does not close the intake port 118 corresponding to the intake passage 115, whereby air of the external environment can flow into the mixing chamber 114 via the intake passage 115. When each cover plate 191 is in the closed position, each cover plate 191 closes the intake port 118 corresponding to the intake passage 115, whereby the rich oil-rich hot gas in the mixing chamber 114 can be prevented from flowing to the outside via the intake passage 115. surroundings. In this embodiment, each of the driving elements 192 is a motor for driving the corresponding cover plate 191 to rotate between an open position and a closed position.

The control device 20 is disposed at an appropriate position of the casing 11, and the control device 20 is electrically connected to the rich oil generator 12, the oxidant injector 172 of the afterburner 17, and the driving elements 192, respectively. The control device 20 is used to control the oxidant injection. The actuator 172 is actuated to inject an oxidant into the mixing chamber 114, and the control device 20 is configured to control each of the drive elements 192 to drive the corresponding cover plate 191 to move between an open position and a closed position. Specifically, the control device 20 of the embodiment includes a controller 201 and an altimeter 202 electrically connected to the controller 201. The controller 201 is electrically connected to the oil-rich gas generator 12, the oxidant injector 172, and the respective driving elements 192, respectively. A predetermined flying height value is preset in the controller 201, and the predetermined flying height value of the embodiment is, for example, 50 kilometers. The altimeter 202 is configured to measure the flying height of the air turbine rocket engine 1 and transmit the measured flying height value to the controller 201 to enable the controller 201 to compare the received flying height value with a predetermined flying height value. . When the flying height value received by the controller 201 is the same as the predetermined flying height value, the controller 201 controls each driving component 192 to drive the corresponding cover plate 191 to move from the open position to the closed position, and at the same time, the controller 201 controls the oxidant injection. The 172 is opened to inject oxidant into the mixing chamber 114, and the controller 201 controls the rich gas generator 12 to increase the flow of oxidant into the combustion chamber 113 within the oxidant cartridge 122 (shown in FIG. 1). Thereby, the control device 20 can automatically simultaneously control the movement of the cover plate 191, open the oxidant injector 172, and control the rich gas generator 12 to increase the oxidant flowing into the combustion chamber 113 in accordance with the actual flying height of the air turbine rocket engine 1. flow.

It should be noted that, in other embodiments, the control device 20 can also be a wireless signal receiver, so that the user can transmit the control signal to the control device 20 by manually operating the remote controller to make the control device The control cover 191 moves, opens the oxidant injector 172, and controls the rich gas generator 12 to increase the flow of oxidant into the combustion chamber 113.

The specific operation of the air turbine rocket engine 1 will be described in detail below:

Referring to Figures 1, 3, 4 and 5, Figure 4 is a flow chart of the operation of the air-turbine rocket engine 1 of the present embodiment. As shown in step S1, when the air-turbine rocket engine 1 is operating in a low-altitude propulsion mode at the beginning, the controller 201 drives the rich-oil generator 12 to operate, and the fuel output from the duct 123 is outputted by the duct 124. The oxidant is first mixed to form an oil-rich gas and then sent to the combustion chamber 113. The rich oil is burned and preheated in the combustion chamber 113 to form an oil-rich hot gas. The combustion chamber 113 provides rich oil hot gas to the turbine 15, and the rich oil hot gas is discharged through the rear exhaust port 116 to propel the turbine 15 to rotate.

In addition, when the air turbine rocket engine 1 is operating in the low altitude propulsion mode, the controller 201 of the control device 20 controls each of the driving elements 192 to drive the corresponding cover plate 191 to move to the open position, so that the intake ports 118 of the respective intake runners 115 Opened. At the same time, the controller 201 will close the oxidant injector 172.

As shown in step S2, when the turbine 15 rotates, a vortex is generated, and the eddy current causes the rich oil to flow into the mixing chamber 114, so that the rich hot gas and the air flowing into the mixing chamber 114 via the intake passage 115 are subjected to the first Mix once to form a mixed oil and gas. Subsequently, the mixed oil and gas passes through the front guide vanes 131, and the flow direction of the mixed oil and gas is guided through the front guide vanes 131, so that the mixed oil and gas can stably flow toward the compressor 16.

As shown in step S3, when the turbine 15 rotates, the compressor 16 is simultaneously rotated by the rotating shaft 14, and the compressor 16 is agitated and pressurized to mix the oil and gas during the rotation of the compressor 16 to perform the second mixing of the mixed oil and gas. The oil and gas in the mixed oil and gas can be fully mixed to increase the mixing efficiency of oil and gas. By the work of the compressor 16, the mixed oil and gas passes through the compressor 16 and becomes a lean and well-mixed mixed oil and gas.

When the well-mixed mixed oil and gas passes through the rear guide vanes 132, the flow guiding direction of the mixed oil and gas is guided through the rear guide vanes 132, so that the mixed oil and gas can stably flow toward the jet flow path 181. Since the mixed oil and gas has been sufficiently mixed before passing through the afterburning device 17, when the mixed oil and gas flows and passes through the afterburning device 17, the design of the flame stabilizer 171 can help the mixed oil and gas achieve near-complete and stable combustion. In order to generate high temperature gas, high combustion efficiency can be achieved.

As shown in step S4, due to the high temperature and high pressure characteristics of the high temperature gas, the high temperature gas can be quickly accelerated when flowing through the nozzle 181, whereby the high temperature gas can be generated after being discharged through the nozzle 181 of the nozzle 18. A lot of thrust to drive the rocket to take off.

It should be noted that the number of the intake air passages 115, the number of the cover plates 191, and the number of the driving elements 192 of the casing 11 may be one or two or more, which may be adjusted according to actual design requirements, and are not disclosed in the embodiment. The number is limited.

Referring to FIG. 1, FIG. 3 and FIG. 6, when the flying height of the air turbine rocket engine 1 reaches a predetermined flying height of, for example, 50 kilometers and the flying speed reaches, for example, Mach 6, the controller 201 receives the flying height value measured by the altimeter 202. The controller 201 controls the driving elements 192 to drive the corresponding cover plate 191 to rotate from the open position to the closed position, so that each cover plate 191 closes the intake corresponding to the intake passage 115. Port 118. At the same time, the controller 201 controls the oxidant injector 172 to open to inject the oxidant into the mixing chamber 114, and the controller 201 controls the rich gas generator 12 to increase the flow of oxidant in the oxidant cylinder 122 into the combustion chamber 113. The air turbine rocket engine 1 is switched from a low altitude propulsion mode to a rocket propulsion mode operation. Thereby, the mixing of fuel and oxidant can be improved to improve the propulsion efficiency of the air turbine rocket engine 1 in the rocket propulsion mode.

Referring to FIG. 7, FIG. 7 is a comparison diagram calculated by computer software, which shows the liquid fuel rocket, the ramjet rocket, and the air turbine rocket engine 1 of the present embodiment respectively with a thrust between 0 and 6 in the flying Mach number. The specific value changes. As can be seen from the comparison of the figures, the thrust ratio of the air turbine rocket engine 1 of the present embodiment is much larger than the thrust ratio of the liquid fuel rocket of 460 seconds between 0 and 6. In the case where the flying Mach number is from 0 to 3, the thrust ratio of the air turbine rocket engine 1 of the present embodiment is also larger than the thrust ratio of the stamping rocket. Thereby, it is understood that the air turbine rocket engine 1 of the present embodiment has a high thrust effect in the low-altitude propulsion mode.

Referring to FIG. 8, in another embodiment of the air turbine rocket engine 1 of the present embodiment, the air turbine rocket engine 1 may also be an auxiliary propulsion engine externally attached to the side of a rocket body 3, thereby increasing the rocket. Propulsion efficiency of the body 3.

Referring to FIG. 9, which is a second embodiment of the air turbine rocket engine of the present invention, the overall structure and operation method of the air turbine rocket engine 1 is substantially the same as that of the first embodiment, except that the air turbine rocket engine 1 of the present embodiment is behind. The burner 17 further includes an igniter 173.

In the present embodiment, the igniter 173 is disposed in the mixing chamber 114 and fixedly coupled to the inner wall surface of the peripheral wall 117 of the casing 11, and the igniter 173 is located at the rear side of the flame stabilizer 171 for flowing to the rear of the flame stabilizer 171. The mixed oil and gas is ignited.

In summary, the air turbine rocket engine 1 of each embodiment is aligned with the rear exhaust port 116 of the combustion chamber 113 by the turbine 15, and the compressor 16 is disposed on the rear side of the turbine 15, so that the turbine 15 can The rich oil hot gas is mixed with the air flowing into the mixing chamber 114 for the first time, and then the compressor 16 can perform the second mixing of the mixed oil and gas, thereby enabling the oil and gas in the mixed oil and gas to be sufficiently mixed. To increase the mixing benefits of oil and gas. When the mixed oil and gas flows to the rear of the afterburning device 17, the mixed oil and gas can be almost completely burned to generate high-temperature gas, whereby high combustion efficiency can be achieved, and the air-turbine rocket engine 1 has high thrust in the low-altitude propulsion mode. The effect is indeed achieved by the object of the present invention.

However, the above is only the embodiment of the present invention, and the scope of the invention is not limited thereto, and all the equivalent equivalent changes and modifications according to the scope of the patent application and the patent specification of the present invention are still The scope of the invention is covered.

1‧‧‧Air Turbine Rocket Engine
11‧‧‧Shell
111‧‧‧ front end
112‧‧‧ Backend
113‧‧‧ combustion chamber
114‧‧‧Mixed chamber
115‧‧‧Intake runner
116‧‧‧ rear exhaust
117‧‧‧Walls
118‧‧‧air inlet
12‧‧‧ Oil-rich gas generator
121‧‧‧fuel storage cylinder
122‧‧‧Oxidizer storage cylinder
123‧‧‧Transport tube
124‧‧‧ delivery tube
13‧‧‧Support frame
131‧‧‧ front guide vane
132‧‧‧ rear guide vane
14‧‧‧ shaft
141‧‧‧ front end
142‧‧‧ Backend
15‧‧‧ turbine
16‧‧‧Compressor
17‧‧‧ Afterburner
171‧‧‧ Flame Stabilizer
172‧‧‧Oxidant injector
173‧‧‧Igniter
18‧‧‧Nozzles
181‧‧‧jet channel
19‧‧‧ valve device
191‧‧‧ cover
192‧‧‧ drive components
20‧‧‧Control device
201‧‧‧ Controller
202‧‧‧ altimeter
3‧‧‧Rocket body
S1~S4‧‧‧ steps

Other features and effects of the present invention will be apparent from the following description of the drawings, wherein: Figure 1 is a schematic diagram of a first embodiment of an air turbine rocket engine of the present invention applied to a rocket, illustrating an air turbine rocket engine 2 is a partial cross-sectional view of the first embodiment; FIG. 3 is a block diagram of the first embodiment, illustrating a control device, an oil-rich gas generator, an oxidant injector, and Figure 4 is a flow chart of the operation of the first embodiment; Figure 5 is an incomplete partial cross-sectional view of the first embodiment illustrating the air turbine rocket engine in a low-altitude propulsion mode In operation, the cover is in the open position; Figure 6 is an incomplete partial cross-sectional view of the first embodiment illustrating the air turbine rocket engine operating in the rocket propulsion mode with the cover in the closed position and the oxidant injector Injecting oxidant into the mixing chamber; Figure 7 is a comparison diagram calculated by computer software, illustrating liquid fuel rocket, stamped rocket and air turbine rocket FIG. 8 is a schematic diagram showing another embodiment of the first embodiment, illustrating that the air turbine rocket engine is externally attached to the side of the rocket body. An auxiliary propulsion engine; and Figure 9 is an incomplete partial cross-sectional view of a second embodiment of the air turbine rocket engine of the present invention.

11‧‧‧Shell

112‧‧‧ Backend

113‧‧‧ combustion chamber

114‧‧‧Mixed chamber

115‧‧‧Intake runner

116‧‧‧ rear exhaust

117‧‧‧Walls

118‧‧‧air inlet

13‧‧‧Support frame

131‧‧‧ front guide vane

132‧‧‧ rear guide vane

14‧‧‧ shaft

141‧‧‧ front end

142‧‧‧ Backend

15‧‧‧ turbine

16‧‧‧Compressor

17‧‧‧ Afterburner

171‧‧‧ Flame Stabilizer

172‧‧‧Oxidant injector

18‧‧‧Nozzles

181‧‧‧jet channel

19‧‧‧ valve device

191‧‧‧ cover

192‧‧‧ drive components

Claims (15)

An air turbine rocket engine comprising: a combustion chamber for providing an oil-rich hot gas, the combustion chamber having a rear exhaust port for discharging the rich oil-heated gas; and a mixing chamber for supplying an air into the air; a turbine disposed in the mixing chamber and aligned with the rear exhaust port, the turbine is configured to drive the rich oil hot gas into the mixing chamber and mix with the air to form a mixed oil and gas; a rotating shaft, including a connection a front end of the turbine, and a rear end opposite to the front end; a compressor disposed in the mixing chamber and connected to the rear end of the rotating shaft, the compressor for agitating and pressurizing the mixed oil and gas; A nozzle is disposed at a rear end of the mixing chamber for discharging high temperature gas generated after the mixed oil and gas is burned. The air turbine rocket engine of claim 1, further comprising a casing forming the combustion chamber and the mixing chamber, the casing forming an intake passage communicating with the mixing chamber, The intake air passage is used to guide the air into the mixing chamber. The air turbine rocket engine of claim 2, further comprising a valve device disposed in the casing for controlling circulation and blocking of the intake runner. The air turbine rocket engine of claim 3, wherein the valve device includes a cover plate for blocking the intake flow passage, and a drive member coupled to the cover plate, the drive member for driving The cover moves between an open position in which the intake passage is not closed and a closed position in which the intake passage is closed. The air turbine rocket engine of claim 4, further comprising a afterburning device disposed in the mixing chamber and located at a rear side of the compressor, the afterburning device including a flame stabilizer, and a device for injecting an oxidant An oxidant injector into the mixing chamber. The air turbine rocket engine of claim 5, further comprising a control device electrically connected to the driving component and the oxidant injector, wherein the control device is configured to control the driving component to drive the cover plate at the opening Moving between the position and the closed position, the control device is configured to control the oxidant injector to act to inject the oxidant, the air turbine rocket engine is operable in a low altitude propulsion mode, and a rocket propulsion mode operates in the low altitude propulsion mode In operation, the control device controls the drive member to drive the cover plate in the open position, the control device controls the oxidant injector to be closed, and when the rocket propulsion mode operates, the control device controls the drive member to drive the cover plate to move to In the closed position, the control device controls the oxidant injector to open to inject the oxidant. The air turbine rocket engine of claim 6, wherein the control device is disposed in the casing and includes a controller, and an altimeter electrically connected to the controller, the controller electrically connecting the oxidant injection And the driving component, the controller is preset with a predetermined flying height value, the altimeter is configured to measure the flying height of the air turbine rocket engine and transmit the measured flying height value to the controller, so that The controller can compare the received flight height value with the predetermined flight altitude value, and when the controller receives the flight height value and the predetermined flight altitude value is the same, the controller controls the driving component The cover plate is driven to move to the closed position and the oxidant injector is controlled to open to inject the oxidant. The air turbine rocket engine of claim 5, wherein the afterburning device further comprises an igniter. The air turbine rocket engine of any one of claims 1 to 8, further comprising an oil-rich gas generator for supplying an oil-rich gas to the combustion chamber, wherein the oil-rich gas passes through The oil-rich hot gas is formed after the combustion chamber is preheated. The air turbine rocket engine of claim 1, further comprising a afterburning device disposed in the mixing chamber and located at a rear side of the compressor, the afterburning device comprising a flame stabilizer, and a device for injecting an oxidant An oxidant injector into the mixing chamber. An air turbine rocket engine operating method comprising the steps of: (A) providing a rich oil-rich gas through a combustion chamber; (B) driving the oil-rich hot gas to a mixing chamber through a turbine to make the oil-rich hot gas Mixing with air flowing into the mixing chamber to form a mixed oil and gas; (C) agitating and pressurizing the mixed oil and gas through a compressor connected to the rear side of the turbine; and (D) burning the mixed oil and gas through a nozzle The high temperature gas generated afterwards is discharged. The method of operating an air turbine rocket engine according to claim 11, wherein in the step (B), the air flows into the mixing chamber via an intake passage communicating with the mixing chamber, when When the air turbine rocket engine is operating in a low altitude propulsion mode, a control device of the air turbine rocket engine controls a cover plate in an open position that does not enclose the intake flow passage. The method of operating an air turbine rocket engine of claim 12, wherein the control device simultaneously controls a compressor located when the control device controls the cover to move to a closed position enclosing the intake runner The oxidant injector on the rear side is opened to inject an oxidant into the mixing chamber to switch the air turbine rocket engine from the low altitude propulsion mode to a rocket propulsion mode. The method of operating an air turbine rocket engine of claim 13, wherein the control device automatically controls movement of the cover plate to the closed position and opens the oxidant injector according to an actual flying height of the air turbine rocket engine. . The method of operating an air turbine rocket engine according to claim 14, wherein the control device comprises a controller, and an altimeter electrically connected to the controller, wherein the controller has a predetermined flying height value preset therein, An altimeter for measuring the flying height of the air turbine rocket engine and transmitting the measured flight height value to the controller to enable the controller to perform the received flying height value and the predetermined flying height value In comparison, when the flight height value received by the controller is the same as the predetermined flight height value, the controller automatically controls the cover to move to the closed position and opens the oxidant injector.