CN114320960A - Tail cooling rotor engine - Google Patents

Abstract

A tail cooling rotor engine is characterized in that a gas compression cavity of a gas compressor A is communicated with a gas collection cavity of an end cover from left to right through a peripheral cold flow channel A of a cold flow tail gas combination, a peripheral cold flow channel B of a jet recoil base and a peripheral cold flow channel C of a main cylinder; the air compression cavity of the air compressor A is communicated with the air collection cavity of the end cover from left to right through the middle cold flow channel A of the cold flow combination, the middle cold flow channel B of the rotor, the middle cold flow channel C of the injection recoil base and the middle cold flow channel D of the main cylinder. The invention has high heat engine efficiency, low requirement on high-temperature performance of blade materials, low rotor rotation speed and large angular momentum, and is suitable for fluid load airplanes and ships and the like.

Description

A tail-cooled rotary engine

technical field

The invention relates to a tail-cooled rotary engine, which belongs to the technical field of gas turbines.

Background technique

In the prior art gas turbine, the main shaft driven by the blades generates torque to drive the load or output power. Due to the structure of the blade, the rotational inertia or angular momentum of the main shaft depends on the high rotational speed. Once the rotational speed drops, the main shaft's ability to drive the load or output power drops sharply or even cannot drive the load. In the prior art gas turbines, the working speed is usually 20,000-50,000 rpm, or even higher. However, high speed must be driven by high-speed gas, and high-speed gas requires high temperature and high pressure, so not only high-speed airflow may lead to incomplete conversion of heat engine efficiency, low thermal efficiency, but also requires blade material with superior high-temperature performance, and the blade temperature can even be as high as 1700 ℃. The high temperature requirement of gas turbines for blade materials is a technical bottleneck restricting the manufacture and development of gas turbines. At the same time, the high speed will inevitably bring about high wear and short overhaul cycle, and increase the maintenance and use costs of users.

In the prior art piston type internal combustion engine, both the crank connecting rod mechanism and the piston have reciprocating motion, and the engine needs to consume a large amount of energy to overcome the reciprocating motion of the piston, and the mechanical loss is extremely large. Therefore, the overall heat engine efficiency of a piston internal combustion engine is extremely low.

In order to overcome the shortcoming of extremely high energy consumption inside the piston internal combustion engine, there are many design cases of the rotary engine in the prior art. For example, in a typical Wankel triangular rotary engine, the rotor rotates unbalanced. Maintaining the unbalanced rotation of the rotor not only consumes a lot of energy, but also the fuel combustion is incomplete, and the exhaust gas pollutes the environment greatly. Its combustion efficiency and thermal cycle efficiency There is great room for improvement.

Another typical type of rotary engine is the turbojet or turbofan engine. However, the turbojet or turbofan engine mainly uses the reaction force of the high-speed jet airflow to propel the flight of special vehicles such as airplanes. When this type of rotary engine is used for shaft output, the high-temperature and high-pressure airflow is self-expanded between the open impeller blades through the expansion of the turbine blades, and a considerable proportion of the gas fails to function. Moreover, the existing turbojet or turbofan engine is only suitable for the fluid load environment, and there is a serious surge phenomenon for the land load, so the high idle speed mode must be used to maintain its stable working state, the thermal cycle efficiency is low, and its fuel consumption is extremely high.

SUMMARY OF THE INVENTION

The purpose of the present invention is to provide a tail-cooled rotary engine with low requirements for high temperature performance of blade material and low rotational speed and high angular momentum.

Technical solution of the present invention

A tail-cooled rotary engine, comprising a compressor A, a rotor B, a burner C, a heat cycle heat exchanger (5) and a preheating air pipe (4); the compressor A comprises an intake hood (1), Bearing A (2), starting clutch (3), housing (17), compressor impeller (18), left side structure of cold flow exhaust gas combination (16) and main shaft (10); the rotor machine B, including cold flow The right side structure of the exhaust gas combination (16), the bearing B (13), the rotor (15), the bearing C (12), the left side structure of the injection recoil seat (6) and the main shaft (10); the burner C, Including the right side structure of the jet recoil seat (6), the main cylinder (7), the burner (14) and the end cover (9); the main cylinder (7) has a main shaft (10) in the middle, and the end The center of the cover (9) is passed through by the main shaft (10) through the bearing D (11); the heat cycle heat exchanger (5) is a tubular structure, including a cold air inlet (5b) and an exhaust gas outlet (5a); From left to right, the compressor chamber (17a) of the compressor A passes through the outer peripheral cold flow channel A (16b) of the cold flow exhaust gas combination (16) and the outer peripheral cold flow cold flow channel B of the jet recoil seat (6). (6a) and the outer peripheral cold flow channel C (7a) of the main cylinder (7) communicate with the air collecting chamber (9a) of the end cover (9); the air compression chamber (17a) of the compressor A is from left to right, Pass through the intermediate cold flow channel A (16c) of the cold flow combination (16), the intermediate cold flow channel B (15e) of the rotor (15), the intermediate cold flow channel C (6c) of the jet recoil seat (6) and the main The intermediate cold flow channel D (7b) of the cylinder body (7) communicates with the gas collecting cavity (9a) of the end cover (9).

In the tail-cooled rotary engine according to the present invention, the intake hood (1) includes a casing (1d) and a guide cone (1d), and the intake passage is divided into a peripheral preheating air passage (1a) and an intermediate cold air passage (1b); the preheating air outlet of the heat cycle heat exchanger (5) is connected to the outer peripheral preheating channel (1a) of the intake hood (1) through the preheating air pipe (4).

In the tail-cooled rotary engine of the present invention, the cold-flow exhaust gas combination (16) has an outer cylinder A (16d), and the inner wall of the left section of the outer cylinder (16d) is connected with a conical guide table (16g) and a guide The flow table extension tube (16h), the conical flow guide table (16g) and the flow guide table extension tube (16h) are provided with a cone (16f); the inner wall of the left section of the outer tube A (16d), the flow guide cone ( 16g) has a baffle plate (16e) on the left side and the outer side of the cone, and the baffle plate (16e) extends leftward to the outer side of the cone (16f) and the extension tube of the baffle (16h). ); the cold flow exhaust gas combination (16) has an annular U-shaped groove composed of an inner tube A (16i1), a middle tube A (16i2) and a bottom (16i3), and the diversion conical platform A flat heat exchange tube (16j) is connected between the opening of (16g) and the opening of the bottom (16i3) of the annular U-shaped groove, the opening of the guide cone (16g), the inner hole of the flat heat exchange tube (16j) and the annular The opening of the U-shaped groove and the opening constitutes the outer peripheral cold flow channel A (16b) of the cold-flow exhaust gas combination (16); the annular U-shaped groove is provided with heat exchange fins (16i4); ), the left side surface of the diversion cone (16g) and the inner wall of the diversion extension tube (16h) and the channel cut off by the diversion rib plate (16e) constitutes the middle of the cold flow exhaust gas combination (16). Cold flow channel A (16c); the annular channel formed between the inner wall of the inner tube A (16i1) of the annular U-shaped groove and the outer wall of the diversion extension tube (16h) is the exhaust port (16a) of the rotor (15). ), the exhaust port (16a) penetrates through the inner surface of the outer cylinder A (16d), the outer surface of the heat exchange flat tube (16j), the right side of the guide cone (16g) and the guide extension tube (16h) the outer side up to the exhaust outlet.

In the tail-cooled rotary engine according to the present invention, the rotor (15) comprises a special-shaped curved tube (15a), a primary hub (15b), a secondary hub (15c), spokes (15f) and recoil blades (15d), The cross-sectional area of the expansion nozzle (15a1) of the special-shaped curved tube (15a) of the rotor (15) is larger than that of the gas injection port (15a2), and the cross-sectional area of the gas injection port (15a2) is larger than that of the necking pipe (15a3) ); the gas injection ports (15a2) of the special-shaped curved pipe (15a) are distributed on the circumference of the primary hub (15b), and the expansion nozzles (15a1) are distributed on the circumference of the right section of the secondary hub (15c); The diameter of the primary hub (15b) is smaller than the diameter of the secondary hub (15c), and the primary hub (15b) and the secondary hub (15c) have an integral structure; the recoil blades (15d) are distributed on the secondary hub (15c). 15c) on the outer circumference of the left section; the inner wall circumference of the secondary hub (15c) is distributed with worm wheel blade-shaped spokes (15f), the gap between two adjacent spokes (15f) and the outer walls of adjacent two special-shaped curved tubes The gap passing through is the intermediate cold flow channel B (15e) of the rotor (15); the fluid contacting the outer side of the rotor (15) from right to left is the high-temperature gas after fuel combustion, and the fluid contacting the inner side from left to right is Preheated pressurized air.

In the tail-cooled rotary engine of the present invention, the annular chassis (6i) of the jet recoil seat (6) is provided with a bell seat (6j), a middle cylinder B (6f) and an outer cylinder B (6g), and the bell There is a shaft hole (6e) at the top center of the base (6j), a diversion recoil pit (6d) on the bottom plate (6i) of the left root of the clock base (6j), The tangential hollow gas injection hole (6b) has a guide rib (6h) between the left outer wall of the bell base (6j) and the inner wall of the middle cylinder B (6f), and between the inner wall of the outer cylinder B (6g) and the middle cylinder A peripheral cold flow channel B(6a) is opened on the chassis (7f) between B(6g), and an intermediate cold flow channel C(6c) is opened around the shaft hole (6e) at the top of the clock base (6j).

In the tail-cooled rotary engine according to the present invention, the main cylinder (7) of the burner C has an outer cylinder C (7i), a middle cylinder C (7j) and an inner cylinder C ( 7k); the right end plate (7f) is annularly distributed with a mounting well (7e) for assembling the burner (14) and an annular fuel groove (7g); the annular fuel groove (7g) of the right end plate (7f) is embedded in the seal; The ring (8) is fixed through the assembly hole (8b) to form an annular fuel passage (8a), and the annular fuel passage (8a) communicates with the fuel inlet (7h); the inner cylinder C (7k) of the main body cylinder (7) ) is the middle cold flow channel D (7b), the outer wall of the inner cylinder C (7k), the left side of the right end plate (7f), the inner wall of the middle cylinder C (7j) and the jet recoil seat (6) The tubular cavity enclosing the city on the right side is the combustion chamber (7c); the tubular cavity between the inner wall of the main body cylinder (7) outer cylinder C (7i) and the inner wall of the middle cylinder (7j) is outside the right end plate (7f). The circumferentially distributed openings communicate with each other to form an outer peripheral cold flow channel C (7a); an air channel (7d) is distributed on the middle circumference of the right end plate (7f) of the main cylinder (7).

In the tail-cooled rotary engine according to the present invention, the burner (14) is a cylindrical structure, and an annular oil groove (14f) is opened on the outer periphery of the middle section of the cylindrical body, and the annular oil groove (14f) is connected to the main cylinder. The annular cavity surrounded by the inner wall of the installation well (7e) of (7) constitutes a fuel ring passage, which communicates with the fuel passage (8a) of the main cylinder (7); the burner (14) The center left section is a conical channel, the right section is a circular tube channel, and a vertebral body (14b) is fixed in the central channel of the left section through a bracket, and the outer peripheral tapered surface of the vertebral body (14b) and the inner tapered surface of the tapered channel The conical passage in between is a compressed air passage (14i), and a fuel oil slit (14g) communicates between the compressed air passage (14i) and the annular oil groove (14f); the center of the cone (14b) is pierced with an igniter (14a) ), the igniter (14a) is pressed by the special-shaped nut (14e); the burner (14) is provided with an annular gap (14h) on the outer periphery of the left end of the cylinder, and the annular gap (14h) is connected to the main body barrel ( 8) The inner wall of the installation well (7e) constitutes a choke section to prevent gas recoil.

In the tail-cooled rotary engine of the present invention, in addition to the centrifugal compressor structure, the compressor A can also adopt another multi-stage axial flow and radial flow mixed structure compressor.

The air inlet hood, the compressor shell, the cold flow exhaust gas combination, the jet recoil seat, the main cylinder and the end cover of the present invention are assembled into a complete machine by flange assembly or welding.

The working process of the present invention

The igniter is energized to light up, the starter motor (not shown) starts and drives the compressor impeller and rotor to rotate. The compressor impeller and rotor spokes press the air into the air collecting cavity, and inject it into the combustion chamber through the conical jet passage of the burner, and at the same time The inhaled fuel is mixed into a fuel-air flammable mixture, which is ignited by the igniter. The high-temperature and high-pressure gas after the fuel is burned is ejected through the gas injection holes to drive the rotor to rotate. When the rotor speed is greater than the starter motor speed and the burner temperature reaches about 600°C, the igniter is turned off, the starter motor stops working and is separated from the main shaft of the engine, and the engine enters the normal operation procedure.

The advantage of the present invention is that

1. The rotor is normalized in cold air cooling, the working temperature is relatively low, the high temperature performance requirements of the rotor blade material are low, and the manufacturing cost is low.

2. Low working speed, low wear and tear, long overhaul cycle and low cost of use.

3. The non-smooth recoil rotor can obtain the effect of low flow and high angular momentum output; at the same time, the fuel is completely burned and the thermal efficiency is high.

4. The recoil rotor performs balanced rotation, which overcomes the shortcomings of high energy consumption of the reciprocating motion of the piston engine and the unbalanced rotation of the Wankel triangular rotor engine, and the engine runs smoothly, with low vibration and low noise.

5. The flywheel function of the large inertia recoil rotor enables the engine to run at low idle speed without surge, especially suitable for ships, low-speed paddle fan aircraft, tanks, range extenders for pure electric vehicles, etc.

Description of drawings

Figure 1 is a schematic elevational sectional view of the present invention.

FIG. 2 is a schematic perspective view of an air intake hood of the present invention.

Fig. 3 is a left side perspective schematic view of the cold flow exhaust gas combination of the present invention.

FIG. 4 is a schematic diagram of an oblique view from the left side of the cross-sectional left side of the cold flow exhaust gas combination of the present invention.

Fig. 5 is a schematic perspective view of the right side of the cold flow exhaust gas combination according to the present invention.

Fig. 6 is a perspective schematic view of the rotor of the present invention viewed obliquely from the right side.

Fig. 7 is a perspective view showing the disassembly of the special-shaped curved pipe in the rotor of the present invention.

FIG. 8 is a perspective schematic view of the left side of the rotor of the present invention.

FIG. 9 is a perspective schematic view of the left side of the jet recoil seat of the present invention.

Figure 10 is a schematic perspective view of the right side of the jet recoil seat of the present invention.

Fig. 11 is a schematic perspective view of a cross-section of the main cylinder of the burner according to the present invention.

Fig. 12 is a schematic perspective view of the fuel seal ring of the present invention in a cross-sectional oblique view.

Fig. 13 is a schematic cross-sectional view of the burner of the present invention.

Implementation

Example 1

As shown in Figures 1-13, a tail-cooled rotary engine includes a compressor A, a rotor B, a burner C, a heat cycle heat exchanger 5 and a preheating air pipe 4; the compressor A includes intake air Cover 1, bearing A2, starting clutch 3, casing 17, compressor impeller 18, left side structure of cold flow exhaust gas combination 16 and main shaft 10; the rotor machine B, including the right side structure of cold flow exhaust gas combination 16, bearings B13, the rotor 15, the bearing C12, the left side structure of the injection recoil seat 6 and the main shaft 10; the burner C includes the right side structure of the injection recoil seat 6, the main cylinder 7, the burner 14 and the end cover 9 There is a main shaft 10 in the middle of the main cylinder body 7, and the center of the end cover 9 has a main shaft 10 through the bearing D11; The compressor chamber 17a of the compressor A passes through the outer peripheral cold flow channel A16b of the cold flow exhaust gas combination 16, the outer peripheral cold flow channel B6a of the jet recoil seat 6 and the outer peripheral cold flow of the main cylinder 7 from left to right. The flow channel C7a communicates with the air collecting chamber 9a of the end cover 9; the air compression chamber 17a of the compressor A passes from left to right through the middle cold flow channel A16c of the cold flow combination 16, the middle cold flow channel B15e of the rotor 15, The intermediate cold flow channel C6c of the jet recoil seat 6 and the intermediate cold flow channel D7b of the main cylinder 7 communicate with the air collecting cavity 9a of the end cover 9 .

Example 2

As shown in Figures 1 and 2, in the tail-cooled rotary engine according to the present invention, the intake hood 1 includes a casing 1d and a guide cone 1d, and the intake passage is divided into a peripheral preheating air passage 1a and an intermediate cooling air Passage 1b; the preheating air outlet of the heat cycle heat exchanger 5 is connected to the outer peripheral preheating passage 1a of the intake hood 1 through the preheating air pipe 4.

Example 3

As shown in Figures 1 and 3-5, in the tail-cooled rotary engine according to the present invention, the cold-flow exhaust gas combination 16 has an outer cylinder A16d, and the inner wall of the left section of the outer cylinder 16d is connected with a conical guide table 16g And the guide table extension tube 16h, the conical guide table 16g and the guide table extension tube 16h have a cone 16f; the inner wall of the left section of the outer cylinder A16d, the left side of the guide cone table 16g and the outer surface of the cone There is a baffle plate 16e on the side, and the baffle plate 16e extends leftward to the outer side of the conical body 16f and the inner side of the baffle extension tube 16h; The annular U-shaped groove formed by the middle cylinder A16i2 and the bottom 16i3, a heat exchange flat tube 16j is connected between the opening of the guide cone 16g and the opening of the bottom 16i3 of the annular U-shaped groove, and the guide cone 16g has an opening. , the opening of the inner hole of the heat exchange flat tube 16j and the annular U-shaped groove constitutes the outer peripheral cold flow channel A16b of the cold flow exhaust gas combination 16; the annular U-shaped groove is provided with heat exchange heat exchange fins 16i4; The outer surface of the conical body 16f, the left side surface of the diversion cone 16g, and the inner wall of the diversion extension cylinder 16h and the channel cut off by the diversion rib plate 16e constitute the intermediate cold flow channel A16c of the cold flow exhaust gas combination 16; The annular channel formed between the inner wall of the inner tube A16i1 of the annular U-shaped groove and the outer wall of the diversion extension tube 16h is the exhaust port 16a of the rotor 15, and the exhaust port 16a passes through the inner side of the outer tube A16d, the heat exchange flat tube The outer surface of 16j, the right side of the guide cone 16g and the outer side of the guide extension tube 16h are up to the exhaust gas outlet.

Example 4

As shown in Figures 1, 6-8, in the tail-cooled rotary engine according to the present invention, the rotor 15 includes a special-shaped curved tube 15a, a primary hub 15b, a secondary hub 15c, spokes 15f and recoil blades 15d. The cross-sectional area of the expansion outlet 15a1 of the special-shaped curved pipe 15a of the rotor 15 is larger than that of the gas injection port 15a2, and the cross-sectional area of the gas injection port 15a2 is larger than the cross-sectional area of the necking pipe 15a3; The injection port 15a2 is distributed on the circumference of the primary hub 15b, and the expansion jets 15a1 are distributed on the circumference of the right section of the secondary hub 15c; the diameter of the primary hub 15b is smaller than the diameter of the secondary hub 15c. 15c is an integral structure; the recoil blades 15d are distributed on the outer circumference of the left section of the secondary hub 15c; the inner wall circumference of the secondary hub 15c is distributed with worm wheel blade-shaped spokes 15f, and the gap between the adjacent two spokes 15f The gap between the outer walls of the adjacent two special-shaped curved tubes is the intermediate cold flow channel B15e of the rotor 15; the fluid contacted by the outer side of the rotor 15 from right to left is the high-temperature gas after fuel combustion, and the inner side of the rotor 15 is contacted from left to right. The fluid is preheated pressurized air.

Example 5

As shown in Figures 1 and 9-10, in the tail-cooled rotary engine according to the present invention, the annular chassis 6i of the jet recoil seat 6 has a bell pedestal 6j, a middle cylinder B6f and an outer cylinder B6g, and the bell pedestal There is a shaft hole 6e in the top center of the bell pedestal 6j, a diversion recoil pit 6d on the chassis 6i at the left root of the bell pedestal 6j, and a tangential hollow gas injection hole 6b on the left root of the bell pedestal 6j. There is a diversion rib 6h between the left outer wall and the inner wall of the middle cylinder B6f, a peripheral cold flow channel B6a is opened on the chassis 7f between the inner wall of the outer cylinder B6g and the middle cylinder B6g, and a shaft hole 6e at the top of the bell base 6j There is an intermediate cold flow channel C6c around it.

Example 6

As shown in Figures 1, 11-13, in the tail-cooled rotary engine according to the present invention, the main cylinder 7 of the burner C has an outer cylinder C7i, a middle cylinder C7j and an inner cylinder C7k on the right end plate 7f ; Described right end plate 7f is annularly distributed with the installation well 7e and annular fuel groove 7g of assembling burner 14; The annular fuel groove 7g of described right end plate 7f is embedded in the sealing ring (8), and is fixed to form annular fuel oil through assembly hole 8b Channel 8a, the annular fuel channel 8a is communicated with the fuel inlet 7h; the inner wall pipeline of the inner barrel C7k of the main body barrel 7 is the intermediate cold flow channel D7b, the outer wall of the inner barrel C7k, the left side of the right end plate 7f, the middle barrel The inner wall of C7j and the tubular cavity surrounded by the right side of the jet recoil seat 6 is the combustion chamber 7c; the tubular cavity between the inner wall of the main body cylinder 7 and the inner wall of the outer cylinder C7i and the inner wall of the middle cylinder 7j and the outer circumference of the right end plate 7f The distributed openings communicate with each other to form an outer peripheral cold flow channel C7a; an air channel 7d is distributed on the middle circumference of the right end plate 7f of the main cylinder body 7 .

Example 7

As shown in FIGS. 1 and 13 , in the tail-cooled rotary engine according to the present invention, the burner 14 is of a cylindrical structure, and an annular oil groove 14f is opened on the outer periphery of the middle section of the cylindrical body. The annular oil groove 14f and The annular cavity surrounded by the inner wall of the mounting well 7e of the main cylinder 7 constitutes a fuel ring, and the fuel ring communicates with the fuel passage 8a of the main cylinder 7; the center left section of the burner 14 is tapered The hole and the right section are round tube holes, and the center hole of the left section is fixed with a vertebral body 14b through a bracket, and the conical channel between the outer peripheral tapered surface of the vertebral body 14b and the inner tapered surface of the tapered hole is the compressed air channel 14i, A fuel slit 14g communicates between the compressed air passage 14i and the annular oil groove 14f; an igniter 14a is pierced through the center of the vertebral body 14b, and the igniter 14a is pressed by a special-shaped nut 14e; the burner 14 is in the cylindrical body An annular notch 14h is formed on the outer periphery of the left end, and the annular notch 14h and the inner wall of the mounting well 7e of the main body barrel 8 form a gas choke to prevent gas recoil.

Example 8

In the tail-cooled rotary engine of the present invention, in addition to the centrifugal compressor structure, the compressor A also adopts another multi-stage axial flow and radial flow mixed structure compressor.

The air inlet hood, the compressor shell, the cold flow exhaust gas combination, the jet recoil seat, the main cylinder and the end cover of the present invention are assembled into a complete machine by flange assembly or welding.

The tail-cooled rotary engine provided by the present invention has been described in detail above. The description of the specific embodiment is only used to help understand the method of the present invention and its core idea. It should be pointed out that for those skilled in the art, without departing from the principle of the present invention, several improvements and modifications can also be made to the present invention, and these improvements and modifications also fall within the protection scope of the claims of the present invention.

Claims (7)

1. A tail-cooled rotary engine, comprising a compressor A, a rotor machine B, a burner C, a heat cycle heat exchanger (5) and a preheating air pipe (4); the compressor A comprises an intake hood (1 ), bearing A (2), starting clutch (3), casing (17), compressor impeller (18), left side structure of cold flow exhaust gas combination (16) and main shaft (10); the rotor machine B, including The right side structure of the cold flow exhaust gas combination (16), the bearing B (13), the rotor (15), the bearing C (12), the left side structure of the injection recoil seat (6) and the main shaft (10); the burner C, including the right side structure of the jet recoil seat (6), the main cylinder (7), the burner (14) and the end cover (9); there is a main shaft (10) in the middle of the main cylinder (7) , the center of the end cover (9) has a main shaft (10) passing through the bearing D (11); the heat cycle heat exchanger (5) is a tube structure, including a cold air inlet (5b), an exhaust gas outlet (5a) ; characterized by: From left to right, the compressor chamber (17a) of the compressor A passes through the outer peripheral cold flow channel A (16b) of the cold flow exhaust gas combination (16) and the outer peripheral cold flow cold flow channel B of the jet recoil seat (6). (6a) and the outer peripheral cold flow channel C (7a) of the main cylinder (7) communicate with the air collecting chamber (9a) of the end cover (9); From left to right, the compressor chamber (17a) of the compressor A passes through the intermediate cold flow passage A (16c) of the cold flow combination (16), the intermediate cold flow passage B (15e) of the rotor (15), and the injection The intermediate cold flow channel C (6c) of the punch seat (6) and the intermediate cold flow channel D (7b) of the main cylinder (7) communicate with the gas collecting cavity (9a) of the end cover (9). 2. The tail-cooled rotary engine according to claim 1, characterized in that: The air intake hood (1) includes a casing (1d) and a guide cone (1d), and the air intake passage is divided into a peripheral preheating air passage (1a) and an intermediate cold air passage (1b); a heat cycle heat exchanger (5) ) of the preheating air outlet is connected to the outer peripheral preheating passage (1a) of the air intake hood (1) through a preheating air pipe (4). 3. The tail-cooled rotary engine according to claim 1, characterized in that: The cold flow exhaust gas combination (16) has an outer cylinder A (16d), and the inner wall of the left section of the outer cylinder (16d) is connected with a conical guide table (16g) and a guide table extension tube (16h). There are cones (16f) in the flow table (16g) and the guide table extension tube (16h); The inner wall of the left section of the outer cylinder A (16d), the left side of the guide cone (16g) and the outer side of the cone are provided with a guide rib (16e), and the guide rib (16e) is directed to the left. extend to the outer side of the cone (16f) and the inner side of the guide table extension cylinder (16h); The cold flow exhaust gas combination (16) has an annular U-shaped groove composed of an inner tube A (16i1), a middle tube A (16i2) and a bottom (16i3). A flat heat exchange tube (16j) is connected between the openings of the bottom (16i3) of the annular U-shaped groove, the opening of the diversion conical table (16g), the inner hole of the flat heat exchange tube (16j) and the ring-shaped U-shaped groove. The opening constitutes the outer peripheral cold flow channel A (16b) of the cold flow exhaust gas combination (16); the annular U-shaped groove is provided with heat exchange heat exchange fins (16i4); The outer surface of the cone (16f), the left side surface of the diversion cone (16g) and the inner wall of the diversion extension cylinder (16h) and the channel cut off by the diversion rib plate (16e) constitute the cold flow exhaust gas combination The intermediate cold flow channel A (16c) of the body (16); The annular channel formed between the inner wall of the inner cylinder A (16i1) of the annular U-shaped groove and the outer wall of the diversion extension cylinder (16h) is the exhaust port (16a) of the rotor (15). ) penetrates through the inner surface of the outer cylinder A (16d), the outer surface of the heat exchange flat tube (16j), the right side of the diversion cone (16g) and the outer surface of the diversion extension tube (16h) until the exhaust gas outlet. 4. The tail-cooled rotary engine according to claim 1, wherein the rotor (15) comprises a special-shaped curved tube (15a), a primary hub (15b), a secondary hub (15c), spokes (15f) and recoil blades (15d), characterized in that: The cross-sectional area of the expansion nozzle (15a1) of the special-shaped curved pipe (15a) of the rotor (15) is larger than the cross-sectional area of the gas injection port (15a2), and the cross-sectional area of the gas injection port (15a2) is larger than that of the necking pipe (15a3) cross-sectional area; The gas injection ports (15a2) of the special-shaped curved pipe (15a) are distributed on the circumference of the primary hub (15b), and the expansion jets (15a1) are distributed on the circumference of the right section of the secondary hub (15c); The diameter of the primary wheel hub (15b) is smaller than the diameter of the secondary wheel hub (15c), and the primary wheel hub (15b) and the secondary wheel hub (15c) have an integral structure; The recoil blades (15d) are distributed on the outer circumference of the left section of the secondary hub (15c); Worm-wheel blade-shaped spokes (15f) are distributed on the circumference of the inner wall of the secondary hub (15c), and the gap between the adjacent two spokes (15f) and the gap between the outer walls of the adjacent two special-shaped curved tubes pass through for the rotor (15). Intermediate cold flow channel B (15e); The fluid contacted by the outer side of the rotor (15) from right to left is high-temperature gas after fuel combustion, and the fluid contacted by the inner side from left to right is preheated pressurized air. 5. The tail-cooled rotary engine according to claim 1, wherein: The annular chassis (6i) of the jet recoil seat (6) is provided with a bell seat (6j), a middle cylinder B (6f) and an outer cylinder B (6g), and the center of the top of the bell seat (6j) has a shaft hole (6j). 6e), there is a diversion recoil pit (6d) on the chassis (6i) at the left root of the bell base (6j), and a tangential hollow gas injection hole (6b) at the left root of the bell base (6j). There is a guide rib (6h) between the left outer wall of the clock base (6j) and the inner wall of the middle tube B (6f), and the chassis (7f) between the inner wall of the outer tube B (6g) and the middle tube B (6g) A peripheral cold flow channel B (6a) is opened on the top, and an intermediate cold flow channel C (6c) is opened around the shaft hole (6e) at the top of the clock base (6j). 6. The tail-cooled rotary engine according to claim 1, characterized in that: the main cylinder (7) of the burner C has an outer cylinder C (7i), a middle cylinder C ( 7j) and the inner cylinder C (7k); the right end plate (7f) is annularly distributed with a mounting well (7e) for assembling the burner (14) and an annular fuel tank (7g); The annular fuel groove (7g) of the right end plate (7f) is embedded in the sealing ring (8), and is fixed through the assembly hole (8b) to form an annular fuel passage (8a), the annular fuel passage (8a) and the fuel inlet (7h) ) is connected; The inner wall pipe of the inner cylinder C (7k) of the main body cylinder (7) is the intermediate cold flow channel D (7b), the outer wall of the inner cylinder C (7k), the left side of the right end plate (7f), the middle cylinder C ( The inner wall of 7j) and the tubular cavity surrounded by the right side of the jet recoil seat (6) is the combustion chamber (7c); The tubular cavity between the inner wall of the main cylinder (7) outer cylinder C (7i) and the inner wall of the middle cylinder (7j) communicates with the openings distributed on the outer circumference of the right end plate (7f) to form an outer peripheral cold flow channel C (7a); Air passages (7d) are distributed on the middle circumference of the right end plate (7f) of the main cylinder body (7). 7. The tail-cooled rotary engine according to claim 1, wherein: The burner (14) has a cylindrical structure, an annular oil groove (14f) is opened on the outer periphery of the middle section of the cylindrical body, and the annular oil groove (14f) is connected to the inner wall of the installation well (7e) of the main cylinder (7). The annular cavity of the besieged city forms a fuel oil ring, and the fuel ring communicates with the fuel passage (8a) of the main cylinder (7); The central left section of the burner (14) is a conical hole, the right section is a circular tube hole, and a vertebral body (14b) is fixed in the central hole of the left section through a bracket, and the outer peripheral conical surface of the vertebral body (14b) The conical passage with the inner conical surface of the conical bore is a compressed air passage (14i), and a fuel oil slit (14g) is communicated between the compressed air passage (14i) and the annular oil groove (14f); An igniter (14a) is pierced through the center of the vertebral body (14b), and the igniter (14a) is pressed by a special-shaped nut (14e); The burner (14) is provided with an annular gap (14h) on the outer periphery of the left end of the cylinder, and the annular gap (14h) and the inner wall of the installation well (7e) of the main body barrel (8) form a choke section for preventing gas recoil .

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