阅读说明：本技术 一种冷转子发动机 (Cold rotor engine ) 是由 李笑一 于 2021-01-06 设计创作，主要内容包括：一种冷转子发动机,其初级压气机A的压气腔8a从右至左通过主筒体7的外周冷流通道A7a、喷射反冲座6的外周冷流通道B6a和换热体4的外周冷流通道C4c与倒向尾盖1的倒向腔1a构成空气左向贯通通道；倒向尾盖1的倒向腔1a从左至右通过换热体4的中间冷流通道A4a、转子22的中间冷流通道B22c、喷射反冲座6的中间冷流通道C6c、三级压气机E的主筒体7的中间压气通道7d、空气喷射罩14的喷射通道14a与主筒体7右端盘7m上的空气喷射口7f构成空气右向贯通通道,空气喷射口7f与喷燃器16的进气口16d对应贯通。转子处于冷空气冷却中,工作温度较低,对转子材质的高温性能要求低,制造成本低廉。(A cold rotor engine, the pressure chamber 8a of the primary compressor A passes through the peripheral cold flow channel A7a of the main cylinder 7, the peripheral cold flow channel B6a of the injection recoil base 6, the peripheral cold flow channel C4C of the heat exchange body 4 and the reverse chamber 1a of the reverse tail cover 1 from right to left to form an air left through channel; the reverse cavity 1a of the reverse tail cover 1 passes through the intermediate cold flow channel A4a of the heat exchange body 4, the intermediate cold flow channel B22C of the rotor 22, the intermediate cold flow channel C6C of the injection recoil base 6, the intermediate air compression channel 7d of the main cylinder 7 of the three-stage compressor E, the injection channel 14a of the air injection cover 14 and the air injection port 7f on the right end disc 7m of the main cylinder 7 from left to right to form an air right through channel, and the air injection port 7f correspondingly penetrates through the air inlet 16d of the burner 16. The rotor is in cold air cooling, the working temperature is lower, the requirement on the high-temperature performance of the rotor material is low, and the manufacturing cost is low.)

1. A cold rotor engine comprises a primary compressor A, a combustor B, a rotor compressor C, a cold flow reversing heat exchanger D, a tertiary compressor E, a tail gas heat exchanger (5) and a preheated air pipe (9);

the primary compressor A comprises an air inlet cover (10), a shell (8), a compressor impeller A (13), a main shaft (2), a bearing A (12) and a starting clutch (11);

the combustor B comprises a right structure of an injection recoil base (6), a main cylinder body (7), a burner (16) and an air injection cover (14);

the rotor compressor C comprises a left side structure of an injection recoil base (6), a rotor (22) with pressure gas vane-shaped spokes, a right side structure of a heat exchange body (4), a main shaft (2), a bearing C (21) and a bearing D (3);

the cold flow reversing heat exchanger D comprises a left exhaust end of a rotor (22), a heat exchange body (4) and a reversing tail cover (1);

the three-stage compressor E comprises an inner cylinder A (7h) of a main cylinder body (7), a main shaft (2), a compressor impeller B (20) and a compressor impeller C (18) which are linked with the main shaft (2), a fixed guide blade A (19) and a fixed guide blade B (17);

the tail gas heat exchanger (5) is of a tube array structure and comprises a cold air inlet (5a) and a tail gas outlet (5b), and preheated air of the tail gas heat exchanger (5) is guided into a primary preheated air inlet (10a) of an air inlet cover (10) through a preheated air pipe (9);

the method is characterized in that:

a pressure air cavity (8a) of the primary compressor A forms an air left-direction through channel from right to left through a peripheral cold flow channel A (7a) of the main cylinder body (7), a peripheral cold flow channel B (6a) of the injection recoil base (6), a peripheral cold flow channel C (4C) of the heat exchange body (4) and a reverse cavity (1a) of the reverse tail cover (1); an inverted cavity (1a) of the inverted tail cover (1) passes through an intermediate cold flow channel A (4a) of a heat exchange body (4), an intermediate cold flow channel B (22C) of a rotor (22), an intermediate cold flow channel C (6C) of an injection back flushing seat (6), an intermediate air compression channel (7d) of a main cylinder body (7) of a three-stage compressor E, an injection channel (14a) of an air injection cover (14) and an air injection port (7f) on a right end disc (7m) of the main cylinder body (7) from left to right to form an air right through channel, and the air injection port (7f) is correspondingly communicated with an air inlet (16d) of a burner (16);

a combustion chamber (7B) of the combustor B passes through a tangential hollowed-out nozzle (6B) of the injection recoil base (6), a gas supply port (22B) of the rotor (22), a reverse joint (22g1), a spray port (22a), a recoil concave (6i) of the injection recoil base (6), a gap between recoil vanes (22f) of the rotor (22), a tail gas cavity (4d) of the heat exchange body (4) and a tail gas channel (4B) from right to left to form a gas through channel.

2. The cold rotor engine of claim 1, wherein:

the air inlet cover (10) comprises a shell (10d) and a flow dividing cone (10c), and an air inlet channel is divided into a preheating air flow channel (10a) and a normal-temperature air flow channel (10 b); the preheating air pipe (9) of the tail gas heat exchanger (5) is communicated with the preheating air flow channel (10a) of the air inlet cover (10).

3. The cold rotor engine of claim 1, wherein:

an inner cylinder A (7h) and a middle cylinder A (7i) are arranged on a right end disc (7m) of a main cylinder body (7) of the combustor B, an outer cylinder A (7j) is arranged on the outer side of the middle cylinder A (7i), and a flow guide rib plate (7k) is arranged between the outer wall of the middle cylinder A (7i) and the inner wall of the outer cylinder A (7j) for supporting; a mounting trap (7e) for mounting a burner (16) and an annular fuel tank (7g) are annularly distributed on the right end disc (7 m); air injection ports (7f) are distributed on the right end disc (7m) corresponding to the mounting well (7 e);

a burner (16) is assembled in the mounting well (7e) of the right end disc (7m), and an air inlet (16d) of the burner (16) corresponds to the air jet opening (7 f);

the tubular cavity enclosed by the outer wall of the inner cylinder A (7h) of the main body cylinder (7), the left side surface of the right end disc (7m), the inner wall of the middle cylinder A (7i) and the right side surface of the injection recoil seat (6) is a combustion chamber (7 b);

a tubular channel formed by a tubular cavity between the inner wall of the outer cylinder A (7j) of the main body cylinder (7) and the outer wall of the middle cylinder A (7i) and the outer circumference of the right end disc (7m) is an outer circumference cold flow channel A (7 a);

the inner wall pipeline of the inner cylinder A (7h) of the main cylinder body (7) is a middle air compressing channel (7d) of the three-stage air compressor E, an air compressing impeller B (20) and an air compressing impeller C (18) which are linked with the main shaft (2) are assembled on the main shaft (2) in the middle air compressing channel (7d), and a fixed guide blade A (19) and a fixed guide blade B (17) are assembled on the inner wall of the inner cylinder A (7 h);

an annular fuel oil groove A (7g) of the right end disc (7m) is embedded into an oil seal ring (15), a spiral fuel oil groove B (15e) is formed in the outer wall of the oil seal ring (15), and a starting point (15d) of the spiral fuel oil groove B (15e) is correspondingly communicated with an oil inlet hole (7c) penetrating through the wall of an outer cylinder A (7j) and the wall of a middle cylinder A (7i) of the main cylinder body (7); the left end face of the oil seal ring (15) is a semicircular fuel oil groove C (15C), and the semicircular fuel oil groove C (15C) is communicated with the terminal of the spiral fuel oil groove B (15 e); a notch (15b) is formed in the semicircular fuel oil groove C (15C) corresponding to an oil inlet groove (16f) of the burner (16), and fuel oil enters the burner (16) through the notch (15 b).

4. The cold rotor engine of claim 1, wherein:

the burner (16) is of a cylinder (16C) structure, an annular oil groove (16f) is formed in the periphery of the middle section of the cylinder, the annular oil groove (16f) and an annular cavity surrounded by the inner wall of a mounting trap (7e) of the main cylinder (7) form a fuel oil annular channel, and the fuel oil annular channel is communicated with a fuel oil inlet hole (7C) through a spiral fuel oil groove B (15e), a semicircular fuel oil groove C (15C) and a notch (15B) of an oil seal ring (15);

the left section of the center of the burner (16) is a conical duct, the right section of the center of the burner is a cylindrical air inlet (16d), a cone (16b) is fixed in the central duct of the left section through a support, a conical channel between the outer peripheral conical surface of the cone (16b) and the inner conical surface of the conical duct is a jet ring (16i), and a fuel slit (16g) is communicated between the jet ring (16i) and an annular oil groove (16 f);

an igniter (16a) penetrates through the center of the cone body (16b), and the igniter (16a) is pressed by a special-shaped nut (16 e);

the burner (16) is provided with an annular notch (16h) at the periphery of the left end of the cylinder, and the annular notch (16h) and the inner wall of the mounting trap (7e) of the main body cylinder (7) form a choke joint for preventing gas from backflushing.

5. The cold rotor engine of claim 1, wherein:

the jet backwash seat is characterized in that a bell seat (6f), a middle cylinder B (6d) and an outer cylinder B (6e) are arranged on an annular chassis (6g) of the jet backwash seat (6), a bearing hole (6h) is formed in the center of the top of the bell seat (6f), a flow guide backwash groove (6i) is formed in the chassis (6g) of the left root of the bell seat (6f), a tangential hollowed-out nozzle (6B) is arranged at the left root of the bell seat (6f), peripheral cold flow channels B (6a) are annularly distributed on the chassis (6g) between the inner wall of the outer cylinder B (6e) and the inner wall of the middle cylinder B (6d), and middle cold flow channels C (6C) are formed around the bearing hole (6h) in the top of the bell seat (6 f).

6. The cold rotor engine as claimed in claim 1, the rotor (22) comprising a profiled curved tube (22g), a primary hub (22h), a secondary hub (22e), spokes (22d) and recoil blades (22f), characterized in that:

the sectional area of a discharge port (22a) of a special-shaped curved pipe (22g) of the rotor (22) is larger than that of a gas feed port (22b), and the sectional area of the gas feed port (22b) is larger than that of a neck pipe (22g 1);

the gas air inlets (22b) of the special-shaped curved pipe (22g) are distributed on the circumference of the first-stage hub (22h), and the spray outlets (22a) are distributed on the circumference of the right section of the second-stage hub (22 e);

the diameter of the first-stage hub (22h) is smaller than that of the second-stage hub (22e), and the first-stage hub (22h) and the second-stage hub (22e) are of an integrated structure or a combined structure;

the recoil blades (22f) are distributed on the outer circumference of the left section of the secondary hub (22 e);

the inner wall of the secondary hub (22e) is distributed with air compression blade-shaped spokes (22d), and a gap between two adjacent spokes (22d) and a gap between the outer walls of two adjacent special-shaped curved tubes (22g) are communicated to form an intermediate cold flow channel B (22c) of the rotor (22);

fluid contacting from right to left in the outer side of the rotor (22) and the pipe of the special-shaped curved pipe (22g) is high-temperature fuel gas after fuel combustion, fluid contacting from left to right is pressurized airflow in the inner sides of the primary hub (22h) and the secondary hub (22e) and the outer side of the special-shaped curved pipe (22 g).

7. The cold rotor engine of claim 1, wherein:

the cold flow reversing heat exchanger D is composed of a reversing tail cover (1), a heat exchange body (4) and a rotor (22) left end structure;

the heat exchange body (4) is provided with an outer cylinder A (4j), the inner wall of the left section of the outer cylinder (4j) is connected with a conical flow guide table (4g) and a flow guide table extension cylinder (4f), and a conical body (4m) is arranged in the conical flow guide table (4g) and the flow guide table extension cylinder (4 f);

a flow guide rib plate (4e) is arranged between the inner wall of the extension cylinder (4f) of the conical flow guide table (4g) and the outer side surface of the conical body (4 m);

the left ends of an inner cylinder B (4h) and a middle cylinder B (4i) of the heat exchange body (4) are connected with a special-shaped heat exchange tube (4k), and the left end of the special-shaped heat exchange tube (4k) is connected to a conical flow guide table (4 g); a peripheral cold flow channel C (4C) of the heat exchange body (4) is formed by a tubular gap between the outer wall of the inner cylinder B (4h) and the inner wall of the middle cylinder B (4i) and an inner channel of the special-shaped heat exchange tube (4 k);

the inner wall cavity of the inner cylinder B (4h) of the heat exchange body (4) is an inner space of a recoil blade (22f) section of the rotor (22), the space between the left end of the rotor (22) and the outer wall of the special-shaped heat exchange tube (4k) is a tail gas cavity (4d), and the tail gas cavity (4d) is communicated with a tail gas channel (4B);

the inverted tail cover (1) is a semicircular arch dish-shaped circular ring with a hollow middle part and comprises a flange plate (1b), a semicircular arch (1d), a hollow-out circle (1c) and an arched downward inverted cavity (1 a).

8. The cold rotor engine of claim 1, wherein:

the rotor compressor C is formed by combining a right side structure of the heat exchange body (4), a rotor (22) with a pressure air blade-shaped spoke (22d), a left side structure of the injection recoil base (6), a main shaft (2), a bearing B (3) and a bearing C (21).

Technical Field

The invention relates to a cold rotor engine, and belongs to the technical field of gas turbines.

Background

In the gas turbine of the prior art, a main shaft driven by blades generates torque to drive load or output power. Because the structure of the blade determines, the rotational inertia or angular momentum of the main shaft depends on high rotating speed, once the rotating speed is low, the load driving capability or output power of the main shaft is sharply reduced, and even the load cannot be driven. In the prior art gas turbine, the working speed is usually 20000-50000rpm or even higher. However, high speed of rotation inevitably requires high speed gas to drive, and high speed gas requires high temperature and high pressure, so that not only high speed gas flow may bring incomplete conversion of heat engine efficiency and low heat efficiency, but also vane material is required to have excellent high temperature performance, and the vane temperature is even up to 1700 ℃. The high temperature requirements of gas turbines for blade materials are a technical bottleneck that limits the manufacturing and development of gas turbines. Meanwhile, high rotating speed inevitably brings high abrasion and short overhaul period, and the maintenance and use cost of a user is increased.

In the piston type internal combustion engine in the prior art, both a crank connecting rod mechanism and a piston do reciprocating motion, and the engine needs to consume a large amount of energy and has great mechanical loss when overcoming the reciprocating motion of the piston. Therefore, the combined heat engine efficiency of the piston type internal combustion engine is extremely low.

In order to overcome the defect of extremely high internal energy consumption of the piston type internal combustion engine, the prior art has various design cases of rotary engines. For example, in a typical wankel triangular rotary engine, the rotor of the engine is unbalanced, and the maintenance of the unbalanced rotation of the rotor not only consumes a large amount of energy, but also causes incomplete fuel combustion and great pollution to the environment by exhaust gas, so that the combustion efficiency and the thermal cycle efficiency of the engine have great improvement space.

Another typical type of rotary engine is a turbojet or turbofan engine. However, the turbojet or turbofan engine mainly pushes the flight of special vehicles such as airplanes and the like by the reaction force of high-speed jet airflow. When such a rotary engine is used for shaft output, a high-temperature and high-pressure gas flow is discharged by self-expansion between the wide impeller blades by the expansion work of the turbine blades, and a considerable proportion of the gas does not function. In addition, the existing turbojet or turbofan engine is only suitable for a fluid load environment, and has a serious surge phenomenon for land load, so that a high idle speed mode is required to be used for maintaining the stable working state of the engine, the thermal cycle efficiency is low, and the oil consumption is extremely high.

Disclosure of Invention

The invention aims to provide a cold rotor engine which has low requirements on high-temperature performance of blade materials and has low rotating speed and large angular momentum.

Technical scheme of the invention

A cold rotor engine comprises a primary compressor A, a combustor B, a rotor compressor C, a cold flow reversing heat exchanger D, a tertiary compressor E, a tail gas heat exchanger and a preheated air pipe; the primary compressor A comprises an air inlet cover, a shell, an air compressing impeller A, a main shaft, a bearing A and a starting clutch; the combustor B comprises a right structure of an injection recoil base, a main cylinder, a burner and an air injection cover; the rotor compressor C comprises a left side structure of an injection recoil seat, a rotor with a pressure gas blade-shaped spoke, a right side structure of a heat exchange body, a main shaft, a bearing C and a bearing D; the cold flow reversing heat exchanger D comprises a left exhaust end of the rotor, a heat exchange body and a reversing tail cover; the three-stage compressor E comprises an inner cylinder A of a main cylinder body, a main shaft, a compressed air impeller B and a compressed air impeller C which are linked with the main shaft, a fixed guide blade A and a fixed guide blade B; the tail gas heat exchanger is of a tubular structure and comprises a cold air inlet and a tail gas outlet, and the preheated air of the tail gas heat exchanger is guided into the primary preheated air inlet of the air inlet cover through a preheated air pipe.

The air compression cavity of the primary air compressor A forms an air left-direction through channel from right to left through the peripheral cold flow channel A of the main cylinder, the peripheral cold flow channel B of the injection recoil base, the peripheral cold flow channel C of the heat exchange body and the reverse cavity of the reverse tail cover; the inverted cavity of the inverted tail cover forms an air right through channel from left to right through an intermediate cold flow channel A of the heat exchange body, an intermediate cold flow channel B of the rotor, an intermediate cold flow channel C of the injection recoil base, an intermediate air compression channel of the main cylinder of the three-stage compressor E, an injection channel of the air injection cover and an air injection port on a right end disc of the main cylinder, and the air injection port is correspondingly communicated with an air inlet of the burner; the combustion chamber of the combustor B forms a fuel gas through channel from right to left through the tangential hollow nozzle of the injection recoil seat, the fuel gas supply port, the inverted joint and the ejection port of the rotor, the recoil recess of the injection recoil seat, the clearance between the recoil blades of the rotor, the tail gas cavity of the heat exchange body and the tail gas channel.

The air inlet cover of the cold rotor engine comprises a shell and a flow dividing cone, wherein an air inlet channel is divided into a preheating air flow channel and a normal-temperature air flow channel; and a preheating air pipe of the tail gas heat exchanger is communicated with a preheating air flow channel of the air inlet cover.

The invention relates to a cold rotor engine.A main cylinder body of a combustor B is provided with an inner cylinder A and a middle cylinder A on a right end disc, the outer side of the middle cylinder A is provided with an outer cylinder A, and a flow guide rib plate is arranged between the outer wall of the middle cylinder A and the inner wall of the outer cylinder A for supporting; an installation trap and an annular fuel tank for assembling a burner are annularly distributed on the right end disc; air jet orifices are distributed on the right end disc corresponding to the mounting wells; a burner is assembled in the mounting well of the right end disc, and an air inlet of the burner corresponds to the air jet; the tubular cavity enclosed by the outer wall of the inner cylinder A of the main body cylinder, the left side surface of the right end disc, the inner wall of the middle cylinder A and the right side surface of the injection recoil seat is a combustion chamber; a tubular channel formed by a tubular cavity between the inner wall of the main barrel outer barrel A and the outer wall of the middle barrel A and the outer circumference of the right end disc is a peripheral cold flow channel A; the inner wall pipeline of the inner cylinder A of the main cylinder body is a middle air compressing channel of the three-stage compressor E, an air compressing impeller B and an air compressing impeller C which are linked with the main shaft are assembled on the main shaft in the middle air compressing channel, and a fixed guide blade A and a fixed guide blade B are assembled on the inner wall of the inner cylinder A;

an annular fuel oil groove A of the right end disc is embedded with an oil seal ring, the outer wall of the oil seal ring is provided with a spiral fuel oil groove B, and the starting point of the spiral fuel oil groove B is correspondingly communicated with an oil inlet hole penetrating through the wall A of the main cylinder outer cylinder and the wall A of the middle cylinder; the left end face of the oil seal ring is a semicircular fuel oil groove C, and the semicircular fuel oil groove C is communicated with the terminal of the spiral fuel oil groove B; and a notch is formed in the semicircular fuel oil tank C corresponding to the oil inlet tank of the burner, and fuel oil enters the burner through the notch.

The cold rotor engine is characterized in that the burner is of a cylindrical structure, an annular oil groove is formed in the periphery of the middle section of the cylinder, the annular oil groove and an annular cavity enclosed by the inner wall of the mounting well of the main cylinder form a fuel oil annular channel, and the fuel oil annular channel is communicated with a fuel oil inlet through a spiral fuel oil groove B, a semicircular fuel oil groove C and a notch of an oil seal ring; the left section of the center of the burner is a conical duct, the right section of the center of the burner is a cylindrical air inlet, a cone is fixed in the central duct of the left section through a bracket, a conical channel between the peripheral conical surface of the cone and the inner conical surface of the conical duct is a jet ring, and a fuel slit is communicated between the jet ring and the annular oil groove; an igniter penetrates through the center of the cone body, and the igniter is tightly pressed through a special-shaped nut; the jet burner is provided with an annular notch at the periphery of the left end of the cylinder, and the annular notch and the inner wall of the mounting well of the main body cylinder form a gas blocking joint for preventing gas from backflushing.

The invention relates to a cold rotor engine, wherein a bell seat, a middle cylinder B and an outer cylinder B are arranged on an annular chassis of a jet recoil seat, a bearing hole is arranged at the center of the top of the bell seat, a flow guide recoil recess is arranged on the chassis of the root part on the left side of the bell seat, a tangential hollowed-out nozzle is arranged on the root part on the left side of the bell seat, peripheral cold flow channels B are annularly distributed on the chassis between the inner wall of the outer cylinder B and the inner wall of the middle cylinder B, and a middle cold flow channel C is arranged around the bearing hole on the top of the bell seat.

The invention relates to a cold rotor engine, wherein a rotor comprises a special-shaped curved pipe, a primary hub, a secondary hub, spokes and recoil blades, the sectional area of a spraying port of the special-shaped curved pipe of the rotor is larger than that of a gas air-feeding port, and the sectional area of the gas air-feeding port is larger than that of a necking pipe; the gas supply ports of the special-shaped curved pipe are distributed on the circumference of the primary hub, and the spray ports are distributed on the circumference of the right section of the secondary hub; the diameter of the primary hub is smaller than that of the secondary hub, and the primary hub and the secondary hub are of an integral structure or a combined structure; the recoil blades are distributed on the outer circumference of the left section of the secondary hub; the inner wall of the secondary hub is distributed with air compression blade-shaped spokes, and a gap between two adjacent spokes and a gap between the outer walls of two adjacent special-shaped curved tubes are communicated to form a middle cold flow channel B of the rotor;

fluid contacting from right to left in the outer side of the rotor and the pipe of the special-shaped curved pipe is high-temperature fuel gas (heat flow) after fuel combustion, and fluid contacting from left to right in the inner sides of the primary hub and the secondary hub and the outer side of the special-shaped curved pipe is pressure air flow (cold flow).

The cold flow reversing heat exchanger D of the cold rotor engine is composed of a reversing tail cover, a heat exchange body and a rotor left end structure; the heat exchanger is provided with an outer cylinder A, the inner wall of the left section of the outer cylinder is connected with a conical flow guide table and a flow guide table extension cylinder, and conical bodies are arranged in the conical flow guide table and the flow guide table extension cylinder; a flow guide rib plate is arranged between the inner wall of the conical flow guide table extension cylinder and the outer side surface of the conical body, and the flow guide rib plate enables airflow to be spirally and rightwards pushed anticlockwise when viewed from left to right; the left ends of the inner cylinder B and the middle cylinder B of the heat exchange body are connected with a special-shaped heat exchange tube, and the left end of the special-shaped heat exchange tube is connected to the conical diversion table; a tubular gap between the outer wall of the inner cylinder B and the inner wall of the middle cylinder B and an inner channel of the special-shaped heat exchange tube form a peripheral cold flow channel C of the heat exchange body; the inner wall cavity of the inner cylinder B of the heat exchange body is the inner space of the backflushing blade section of the rotor, the space between the left end of the rotor and the outer wall of the special-shaped heat exchange tube is a tail gas cavity, and the tail gas cavity is communicated with a tail gas channel; the inverted tail cover is a semicircular arched dish-shaped ring with a hollow middle part and comprises a flange plate, a semicircular arch, a hollow-out circle and an arched inverted cavity.

The invention relates to a cold rotor engine, wherein a rotor compressor C is formed by combining a right side structure of a heat exchange body, a rotor with a compression blade-shaped spoke, a left side structure of an injection recoil seat, a main shaft, a bearing B and a bearing C; the rotor rotates clockwise as viewed from left to right, pushing the preheated air flow from left to right.

The invention relates to an air inlet cover, a shell, a main cylinder body, an injection recoil base, a heat exchange body and a guide end cover which are assembled into a whole machine through flange plate assembly or welding.

The present invention does not show an oil supply system and an ignition system.

Working process of the invention

The igniter is electrified to be lighted, a starting motor (not shown) is started and drives the air compressing impeller and the rotor to rotate, the spokes of the air compressing impeller and the rotor spray air into the combustion chamber through the conical air spraying channel of the burner, and simultaneously, fuel is sucked to be mixed into fuel-air combustible mixed gas which is ignited through the igniter. The high-temperature and high-pressure fuel gas after the fuel combustion is sprayed out through the fuel gas spraying hole to drive the rotor to rotate. When the rotating speed of the rotor is greater than that of the starting motor and the temperature of the combustor reaches about 600 ℃, the igniter is closed, the starting motor stops working and is separated from the main shaft of the engine, and the engine enters a normal operation program. When the air pushed by the primary compressor E flows through the rotor of the rotor compressor C, the rotor is cooled, the temperature of the rotor is ensured not to exceed 700 ℃, and the engine can be manufactured by using common high-temperature alloy steel materials.

The invention has the advantages that

1. The rotor is in cold air cooling in a normalized state, the working temperature is relatively low, the requirement on the high-temperature performance of the rotor blade material is low, and the manufacturing cost is low.

2. Low working speed, small abrasion, long overhaul period and low use cost.

3. The rotor is not smoothly recoiled, and the output effects of low flow and high angular momentum can be obtained; meanwhile, the fuel is completely combusted, and the heat efficiency is high.

4. The rotor rotates in a balanced manner, the defect of high energy consumption of reciprocating motion of a piston engine and unbalanced rotation of a Wankel triangle rotor engine is overcome, and the engine is stable in operation, small in vibration and low in noise.

5. The flywheel function of the large inertia recoil rotor enables the engine to run at low idle speed without surge, and is particularly suitable for range extenders of ships, low-speed propeller aircrafts, tanks and pure electric vehicles.

Drawings

FIG. 1 is a schematic cross-sectional elevation view of the present invention.

Fig. 2 is a perspective oblique view schematic diagram of the intake shroud of the present invention.

FIG. 3 is a left oblique perspective view of the main cylinder of the present invention.

FIG. 4 is a schematic perspective view of the main cylinder body of the present invention viewed obliquely from the right.

Fig. 5 is an oblique perspective view schematically showing the oil seal ring of the present invention.

Fig. 6 is a schematic cross-sectional view of a burner of the present invention.

Fig. 7 is a perspective view of the jet recoil base of the present invention from a lower right perspective.

Fig. 8 is a perspective view of the spray recoil base of the present invention from an upper left oblique view.

Fig. 9 is a perspective view of the rotor of the present invention viewed obliquely from the top left.

Fig. 10 is a perspective view of the rotor of the present invention from the right oblique view.

Fig. 11 is a perspective oblique view of the rotor of the present invention.

FIG. 12 is a schematic left oblique perspective view of a heat exchange body of the present invention in cross section.

FIG. 13 is a schematic cross-sectional right oblique perspective view of a heat exchanger according to the present invention.

FIG. 14 is a cut-away, left oblique perspective view of the tailgate with the full contents of the tailgate.

Detailed description of the preferred embodiments

Example 1

As shown in the attached figures 1-14, a cold rotor engine comprises a primary compressor A, a combustor B, a rotor compressor C, a cold flow reversing heat exchanger D, a tertiary compressor E, a tail gas heat exchanger 5 and a preheated air pipe 9; the primary compressor A comprises an air inlet cover 10, a shell 8, a compressor impeller A13, a main shaft 2, a bearing A12 and a starting clutch 11; the combustor B comprises a right structure of an injection recoil base 6, a main cylinder 7, a burner 16 and an air injection cover 14; the rotor compressor C comprises a left side structure of an injection recoil base 6, a rotor 22 with pressure gas vane-shaped spokes, a right side structure of a heat exchange body 4, a main shaft 2, a bearing C21 and a bearing D3; the cold flow reversing heat exchanger D comprises a left exhaust end of the rotor 22, a heat exchange body 4 and a reversing tail cover 1; the three-stage compressor E comprises an inner cylinder A7h of a main cylinder body 7, a main shaft 2, a compressor impeller B20 and a compressor impeller C18 which are linked with the main shaft 2, a fixed guide blade A19 and a fixed guide blade B17; the tail gas heat exchanger 5 is of a tubular structure and comprises a cold air inlet 5a and a tail gas outlet 5b, and preheated air of the tail gas heat exchanger 5 is guided into a primary preheated air inlet 10a of an air inlet cover 10 through a preheated air pipe 9; the air compression cavity 8a of the primary compressor A forms an air left-direction through channel from right to left through the peripheral cold flow channel A7a of the main cylinder 7, the peripheral cold flow channel B6a of the injection recoil base 6, the peripheral cold flow channel C4C of the heat exchange body 4 and the reverse cavity 1a of the reverse tail cover 1; the reverse cavity 1a of the reverse tail cover 1 passes through the middle cold flow channel A4a of the heat exchange body 4, the middle cold flow channel B22C of the rotor 22, the middle cold flow channel C6C of the injection recoil base 6, the middle air compression channel 7d of the main cylinder 7 of the three-stage compressor E, the injection channel 14a of the air injection cover 14 and the air injection port 7f on the right end disc 7m of the main cylinder 7 from left to right to form an air right through channel, and the air injection port 7f is correspondingly communicated with the air inlet 16d of the burner 16; the combustion chamber 7B of the combustor B passes through the tangential hollow nozzle 6B of the injection recoil base 6, the gas supply port 22B of the rotor 22, the reverse joint 22g1, the spray port 22a, the recoil recess 6i of the injection recoil base 6, the clearance between the recoil vanes 22f of the rotor 22, and the tail gas cavity 4d and the tail gas channel 4B of the heat exchange body 4 from right to left to form a gas through channel.

Example 2

As shown in fig. 1 and 2, the air intake cover 10 of the cold rotary engine includes a housing 10d and a splitter cone 10c, and the air intake passage is divided into a preheating air flow passage 10a and a normal temperature air flow passage 10 b; the preheated air pipe 9 of the tail gas heat exchanger 5 is communicated with a preheated air flow passage 10a of an air inlet cover 10.

Example 3

As shown in fig. 1 and 3-6, in the cold rotor engine, the main cylinder 7 of the combustor B is provided with an inner cylinder A7h and a middle cylinder A7i on a right end disc 7m, the outer side of the middle cylinder A7i is provided with an outer cylinder A7j, and a flow guide rib plate 7k is arranged between the outer wall of the middle cylinder A7i and the inner wall of the outer cylinder A7j for supporting; a mounting well 7e and an annular fuel tank 7g for mounting a burner 16 are annularly distributed on the right end disc 7 m; air injection ports 7f are distributed on the right end disc 7m corresponding to the mounting wells 7 e; a burner 16 is arranged in the mounting well 7e of the right end disc 7m, and an air inlet 16d of the burner 16 corresponds to the air injection port 7 f; the tubular cavity enclosed by the outer wall of the inner cylinder A7h of the main body cylinder 7, the left side surface of the right end disc 7m, the inner wall of the middle cylinder A7i and the right side surface of the injection recoil seat 6 is a combustion chamber 7 b; the tubular cavity between the inner wall of the outer cylinder A7j of the main body cylinder 7 and the outer wall of the middle cylinder A7i and the tubular channel formed by the outer circumference of the right end disc 7m are outer circumference cold flow channels A7 a: an inner wall pipeline of an inner cylinder A7h of the main cylinder body 7 is a middle air compressing channel 7d of the three-stage compressor E, an air compressing impeller B20 and an air compressing impeller C18 which are linked with the main shaft 2 are assembled on the main shaft 2 in the middle air compressing channel 7d, and a fixed guide blade A19 and a fixed guide blade B17 are assembled on the inner wall of the inner cylinder A7 h; an annular fuel oil groove A7g of the right end disc 7m is embedded into an oil seal ring 15, the outer wall of the oil seal ring 15 is provided with a spiral fuel oil groove B15e, and the initial point 15d of the spiral fuel oil groove B15e is correspondingly communicated with an oil inlet hole 7c penetrating through the wall of an outer cylinder A7j of the main cylinder 7 and the wall of an inner cylinder A7 i; the left end surface of the oil seal ring 15 is a semicircular fuel oil groove C15C, and the semicircular fuel oil groove C15C is communicated with the terminal end of a spiral fuel oil groove B15 e; a notch 15b is formed on the semicircular fuel tank C15C corresponding to the oil inlet groove 16f of the burner 16, and fuel enters the burner 16 through the notch 15 b.

Example 4

As shown in fig. 1 and 6, in the cold rotor engine, the burner 16 is a cylindrical body 16C structure, an annular oil groove 16f is formed on the outer periphery of the middle section of the cylindrical body, the annular oil groove 16f and an annular cavity surrounded by the inner wall of the mounting trap 7e of the main cylinder 7 form a fuel oil ring, and the fuel oil ring is communicated with a fuel oil inlet hole 7C through a spiral fuel oil groove B15e, a semicircular fuel oil groove C15C and a notch 15B of the oil seal ring 15; the left section of the center of the burner 16 is a conical duct, the right section of the center of the burner is a cylindrical air inlet 16d, a cone 16b is fixed in the central duct of the left section through a bracket, a conical channel between the peripheral conical surface of the cone 16b and the inner conical surface of the conical duct is an air injection ring 16i, and a fuel slit 16g is communicated between the air injection ring 16i and the annular oil groove 16 f; an igniter 16a penetrates through the center of the cone 16b, and the igniter 16a is pressed by a special-shaped nut 16 e; the burner 16 is provided with an annular gap 16h at the periphery of the left end of the cylinder, and the annular gap 16h and the inner wall of the mounting trap 7e of the main body cylinder 7 form a choke joint for preventing gas from backflushing.

Example 5

As shown in fig. 1 and 7-8, in the cold rotor engine, a ring-shaped chassis 6g of the injection recoil base 6 is provided with a clock base 6f, a middle cylinder B6d and an outer cylinder B6e, the top center of the clock base 6f is provided with a bearing hole 6h, the chassis 6g at the root part of the left side of the clock base 6f is provided with a flow guide recoil recess 6i, the root part of the left side of the clock base 6f is provided with a tangential hollowed nozzle 6B, a peripheral cold flow channel B6a is annularly distributed on the chassis 6g between the inner wall of the outer cylinder B6e and the inner wall of the middle cylinder B6d, and a middle cold flow channel C6C is arranged around the bearing hole 6h at the top of the clock base 6 f.

Example 6

As shown in fig. 1, 9-10, 12-14, the cold rotary engine, the cold flow reversing heat exchanger D, is composed of a reversing tail cover 1, a heat exchange body 4 and a rotor 22 left end structure; the heat exchanger 4 is provided with an outer cylinder A4j, the inner wall of the left section of the outer cylinder 4j is connected with a conical guide table 4g and a guide table extension cylinder 4f, and a conical body 4m is arranged in the conical guide table 4g and the guide table extension cylinder 4 f; a flow guide rib plate 4e is arranged between the inner wall of the extension cylinder 4f of the conical flow guide table 4g and the outer side surface of the conical body 4m, and the flow guide rib plate 4e enables airflow to be spirally and rightwards pushed anticlockwise when viewed from left to right; the left ends of the inner cylinder B4h and the middle cylinder B4i of the heat exchanger 4 are connected with a special-shaped heat exchange tube 4k, and the left end of the special-shaped heat exchange tube 4k is connected to a conical flow guide table 4 g; a tubular gap between the outer wall of the inner cylinder B4h and the inner wall of the middle cylinder B4i and an inner channel of the special-shaped heat exchange tube 4k form a peripheral cold flow channel C4C of the heat exchanger 4; the inner wall cavity of the inner cylinder B4h of the heat exchange body 4 is an inner space of the backflushing blade 22f section of the rotor 22, the space between the left end of the rotor 22 and the outer wall of the special-shaped heat exchange tube 4k is a tail gas cavity 4d, and the tail gas cavity 4d is communicated with the tail gas channel 4B; the inverted tail cover 1 is a semicircular arched saucer-shaped circular ring with a hollow middle part and comprises a flange plate 1b, a semicircular arch 1d, a hollow circle 1c and an arched inverted cavity 1 a.

Example 7

Referring to fig. 1, 9-10, the said cold rotor engine, the said rotor 22 includes the special curved tube 22g, first-stage hub 22h, second-stage hub 22e, spoke 22d and recoil vane 22f, the sectional area of the outlet 22a of the special curved tube 22g of the said rotor 22 is greater than the sectional area of the gas admission port 22b, the sectional area of the gas admission port 22b is greater than the sectional area of the neck pipe 22g 1; the gas air inlets 22b of the special-shaped curved pipe 22g are distributed on the circumference of the primary hub 22h, and the spray outlets 22a are distributed on the circumference of the right section of the secondary hub 22 e; the diameter of the first-stage hub 22h is smaller than that of the second-stage hub 22e, and the first-stage hub 22h and the second-stage hub 22e are of an integral structure or a combined structure; the recoil vanes 22f are distributed on the outer circumference of the left section of the secondary hub 22 e; the inner wall of the secondary hub 22e is distributed with air pressure blade-shaped spokes 22d, and a gap between two adjacent spokes 22d and a gap between the outer walls of two adjacent special-shaped curved tubes 22g are communicated to form a middle cold flow channel B22c of the rotor 22; the fluid contacting from right to left in the outer side of the rotor 22 and the tube of the special-shaped curved tube 22g is high-temperature gas (heat flow) after fuel combustion, and the fluid contacting from left to right in the inner sides of the primary hub 22h and the secondary hub 22e and the outer side of the special-shaped curved tube 22g is pressure air flow (cold flow).

Example 8

As shown in fig. 1, 12-13, the cold rotor engine has a rotor compressor C formed by combining the right structure of the heat exchanger 4, the rotor 22 with the pressure-fan-shaped spokes 22d, the left structure of the injection recoil base 6, the main shaft 2, a bearing B3 and a bearing C21; the rotor 22 rotates clockwise as viewed from left to right, pushing the preheated air flow from left to right.

The invention relates to an air inlet cover, a shell, a main cylinder body, an injection recoil base, a heat exchange body and a guide end cover which are assembled into a whole machine through flange plate assembly or welding.

The present invention does not show an oil supply system and an ignition system.

The cold rotor engine provided by the invention is described in detail above. The description of the specific embodiments is only intended to facilitate an understanding of the method of the invention and its core ideas. It should be noted that, for those skilled in the art, without departing from the principle of the present invention, several improvements and modifications can be made to the present invention, and these improvements and modifications also fall into the protection scope of the claims of the present invention.