A rotary combustion device with shaft power and thrust coupled output

Abstract

The present invention discloses a rotary combustion device for outputting shaft power and thrust coupled, comprising a front hollow shaft, an inclined nozzle, a quick-plug ignition nozzle, a combustion chamber and a rear hollow shaft; the front hollow shaft and the rear hollow shaft are respectively located at the two ends of the combustion chamber, and the front hollow shaft, the rear hollow shaft and the combustion chamber are coaxial; one end of the front hollow shaft extends into the combustion chamber, and a section of the front hollow shaft extending into the combustion chamber is evenly provided with a plurality of nozzles in the circumferential direction, and a baffle is provided at the end of the front hollow shaft extending into the combustion chamber to block the internal chamber of the front hollow shaft; the front hollow shaft is used to introduce fuel, and the rear hollow shaft is used to introduce air; a plurality of inclined nozzles are installed on the periphery of the combustion chamber and are evenly distributed; the quick-plug ignition nozzle is also fixedly connected to the periphery of the combustion chamber. The present invention has high working reliability, high combustion efficiency, can adjust the output of thrust and rotation torque of different sizes, and is light in weight.

Description

Technical Field

[0001] The invention belongs to the field of aerospace propulsion theory and engineering, and in particular relates to a rotary combustion device with shaft power and thrust coupled output. Background Art

[0002] With the frequent development of space activities, new requirements for future space transportation have been put forward, including low-cost space launch, high-reliability round-trip between space and air, fast response and convenient use, and flight-based space and air flights. At present, the space transportation systems in service in the world are mainly disposable rockets, which are expensive. Therefore, it is urgent to develop a new generation of reusable space transportation systems, form space flights, enhance the ability of high-reliability and fast-response round-trip transportation between space and air, and promote high-frequency, large-scale space activities and space economy. Reusable space transportation systems can be divided into two categories according to the form of power: rocket power and combined power. Among them, the reusable space transportation system based on combined power adopts an air-breathing combined engine and a lifting body configuration, which can fly freely between dense atmosphere, near space, and orbital space. In recent years, it has become a research hotspot for future reusable space transportation systems and has received high attention. Existing space propulsion systems, including various types of aircraft engines, rocket engines, ramjet engines, and piston engines, all have their own performance advantages and ideal flight airspace. The operation of rocket engines is not limited by altitude and initial velocity conditions, but the performance is low and the propellant consumption rate is large; the characteristics of aircraft engines are high performance, but they are limited by the temperature resistance limit of the turbine. The temperature limit of the turbine has always been the core constraint factor for improving the efficiency of the engine's thermal cycle. As the incoming air temperature increases during high-speed flight, the impact of the turbine temperature limit on the thermal cycle efficiency becomes more critical, and even becomes the key to determining whether the thermal cycle method is feasible. In order to increase the flight speed limit of the turbine engine, introducing a gas generator to generate gas to replace the high-temperature incoming air is a feasible solution for high-speed flight, namely the air-turbine-rocket combined cycle engine solution. However, another prominent problem of this engine is that it is difficult to take into account the overall performance under high and low-speed flight. The temperature limit of the turbine is still the key factor that restricts the operating temperature of the gas generator and thus restricts the improvement of the engine's thermal cycle efficiency. Summary of the invention

[0003] In view of the defects of the prior art, the present invention provides a rotary combustion device with coupled output of shaft power and thrust, which can solve the problem that the temperature limit of the existing engine turbine seriously restricts the thermal cycle efficiency, increase the working temperature of the gas generator and thus increase the output power of the engine, can output shaft power and thrust at the same time, has a simple structure and high reliability.

[0004] The purpose of the present invention is achieved through the following technical solutions:

[0005] A rotary combustion device with shaft power and thrust coupled output, comprising a front hollow shaft, an inclined nozzle, a quick-plug ignition nozzle, a combustion chamber and a rear hollow shaft;

[0006] The front end hollow shaft and the rear end hollow shaft are respectively located at the two ends of the combustion chamber, and the front end hollow shaft, the rear end hollow shaft and the combustion chamber are coaxial; one end of the front end hollow shaft extends into the combustion chamber, and a plurality of nozzles are evenly arranged in the circumference of the section where the front end hollow shaft extends into the combustion chamber, and a baffle is provided at the end where the front end hollow shaft extends into the combustion chamber to block the internal cavity of the front end hollow shaft;

[0007] The front hollow shaft is used for introducing fuel, and the rear hollow shaft is used for introducing air;

[0008] A plurality of the inclined nozzles are evenly distributed on the combustion chamber along the circumferential direction;

[0009] The quick-plug ignition nozzle is also fixedly connected to the outer periphery of the combustion chamber.

[0010] Furthermore, the front end hollow shaft, the baffle and the combustion chamber are integrally formed by additive manufacturing technology.

[0011] Furthermore, there are three inclined nozzles, which are evenly arranged on the end surface of the combustion chamber close to the front hollow shaft.

[0012] Furthermore, there are two quick-plug ignition nozzles, which are symmetrically arranged on the periphery of the combustion chamber.

[0013] Furthermore, the front end hollow shaft and the rear end hollow shaft are both stepped shafts with multiple shoulders.

[0014] The beneficial effects of the present invention are as follows:

[0015] 1. The rotary combustion device of the present invention adopts a method of separate air intake at both ends of the axis, and the fuel and gas are separated, which has a simple structure and can prevent leakage in a rotating state, thereby improving working reliability; since the air is at the low-temperature end and the fuel is at the high-temperature end, it is helpful to increase the temperature of the fuel, improve the combustion efficiency, and thus improve the output power.

[0016] 2. The rotary combustion device of the present invention rotates at high speed in the working state, driving the fuel to rotate together in the fuel chamber, and then spraying out from the nozzle; this fuel supply method can achieve efficient atomization of the fuel under a relatively small fuel supply pressure, which helps to reduce accessories such as booster pumps and reduce weight.

[0017] 3. The rotary combustion device of the present invention discharges the gas through the inclined nozzle. This method can generate thrust and rotation torque of different magnitudes by adjusting the outlet axis direction of the inclined nozzle during design. When the outlet axis is close to the circumference of the combustion chamber, a larger torque is generated. When the outlet axis is axial, the axial thrust generated is the largest.

[0018] 4. The rotary combustion device of the present invention adopts a quick-plug ignition nozzle, and the connection between the ignition nozzle and the ignition cable is a quick plug, which can be quickly and conveniently disconnected. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 It is an isometric diagram of a rotary combustion device according to an embodiment of the present invention.

[0020] Figure 2 It is an AA cross-sectional view of a rotary combustion device according to an embodiment of the present invention.

[0021] Figure 3 BB cross-sectional view of the rotary combustion device according to an embodiment of the present invention.

[0022] In the figure, there are a front hollow shaft 1, an inclined nozzle 2, a quick-plug ignition nozzle 3, a combustion chamber 4, a rear hollow shaft 5, a fuel inlet cavity 1-1, a front bearing end face 1-2, a nozzle 1-3, a baffle 1-4, an air inlet cavity 5-1, and a rear bearing end face 5-2. DETAILED DESCRIPTION

[0023] The present invention will be described in detail below based on the accompanying drawings and preferred embodiments, and the purpose and effects of the present invention will become more clear. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not used to limit the present invention.

[0024] See also Figure 1 The rotary combustion device for outputting shaft work and thrust proposed in the embodiment of the present invention comprises a front hollow shaft 1, an inclined nozzle 2, a quick-plug ignition nozzle 3, a combustion chamber 4 and a rear hollow shaft 5.

[0025] The front hollow shaft 1 and the rear hollow shaft 5 are respectively located at the two ends of the combustion chamber 4, and the front hollow shaft 1, the rear hollow shaft 5 and the combustion chamber 4 are coaxial. Figure 2 As shown, one end of the front hollow shaft 1 extends into the combustion chamber 4, and a plurality of nozzles 1-3 are evenly arranged in the circumference of the section where the front hollow shaft 1 extends into the combustion chamber 4, and a baffle 1-4 is provided at the end where the front hollow shaft 1 extends into the combustion chamber 4 to block the internal chamber of the front hollow shaft 1. Figure 2 As shown, the front hollow shaft 1, baffles 1-4 and combustion chamber 4 are integrally formed by additive manufacturing technology, which can reduce manufacturing costs, reduce the number of parts and components, and improve their working stability.

[0026] like Figure 3 As shown, three inclined nozzles 2 are evenly distributed along the circumferential direction on the end surface of the combustion chamber 4 close to the front end hollow shaft 1.

[0027] like Figure 3 As shown, there are two quick-plug ignition nozzles 3, which are axially symmetrically arranged on the outer periphery of the combustion chamber 4 and fixed to the outer peripheral surface of the combustion chamber 4 through the external threads of the quick-plug ignition nozzles 3. This arrangement of the quick-plug ignition nozzles 3 can effectively reduce the vibration of the rotary gas generator when it rotates at high speed.

[0028] like Figure 2 As shown, both the front hollow shaft 1 and the rear hollow shaft 5 are stepped shafts with multiple shoulders. The front hollow shaft 1 is used to introduce fuel, and the fuel enters the combustion chamber 4 through the fuel inlet cavity 1-1 inside the front hollow shaft 1. The rear hollow shaft 5 is used to introduce air.

[0029] The rotary combustion device is connected to the bearing through the front bearing end face 1 - 2 on the front hollow shaft 1 and the rear bearing end face 5 - 2 of the rear hollow shaft 5 .

[0030] The working principle of the rotary combustion device of the embodiment of the present invention is as follows:

[0031] The fuel enters the combustion chamber 4 through the fuel inlet cavity 1-1, and is sprayed into the combustion chamber 4 through four nozzles 1-3 under the condition of high-speed rotation of the rotary combustion device. At the same time, the air enters the combustion chamber 6 through the air inlet cavity 5-1 of the rear hollow shaft 5. At this time, a large number of low-speed recirculation areas are generated behind the baffle 1-4, and the fuel atomized by the nozzle 1-3 is fully mixed with the air in the low-speed recirculation area. At this time, the quick-plug ignition nozzle 3 is ignited to ignite the combustible gas; after the combustible gas is ignited, the cable is disconnected from the ignition nozzle body through the quick plug-in switch 3-1 on the quick-plug ignition nozzle 3; the combustible gas burns in the combustion chamber 4 and generates high-temperature and high-pressure gas, which is sprayed out through three inclined nozzles 2 evenly arranged circumferentially, generating radial torque and axial thrust to drive the rotary combustion device to rotate and generate thrust.

[0032] The rotary combustion device of the present invention discharges the gas through the inclined nozzle 2. This method can generate thrust and rotation torque of different magnitudes by adjusting the outlet axis direction of the inclined nozzle during design. When the outlet axis is close to the circumference of the combustion chamber, a larger torque is generated. When the outlet axis is axial, the axial thrust generated is the largest.

[0033] The working steps of the rotary combustion device of the present embodiment are as follows:

[0034] 1. Connect the cable of the igniter to the quick-plug ignition nozzle 3 through the quick plug 5-1 on the quick-plug ignition nozzle 3, and start to energize the quick-plug ignition nozzle 3.

[0035] 2. By adjusting the opening of the fuel valve and the air valve, a certain mass flow rate and pressure of gas is adjusted to enter the combustion chamber 4. At this time, the mixed gas is easily ignited by the quick-plug ignition nozzle 3 and can burn stably. Since the quick-plug ignition nozzle 3 has not been disconnected from the cable, the rotary gas generator cannot start rotating.

[0036] 3. Turn off the power supply of the quick-plug ignition nozzle 3, quickly separate the ignition cable from the ignition nozzle through the connecting wire, then increase the opening of the fuel valve and the air valve to increase the gas flow and pressure entering the combustion chamber 4. At this time, the high-temperature and high-pressure gas generated is ejected through the inclined nozzle 2, driving the rotating combustion device to rotate and generate thrust.

[0037] 4. During design, the thrust and rotational torque generated can be adjusted by adjusting the outlet axis direction of the inclined nozzle 2.

[0038] Those skilled in the art can understand that the above are only preferred examples of the invention and are not intended to limit the invention. Although the invention is described in detail with reference to the above examples, those skilled in the art can still modify the technical solutions recorded in the above examples or replace some of the technical features therein with equivalents. Any modification, equivalent replacement, etc. made within the spirit and principle of the invention shall be included in the protection scope of the invention.

Claims

1. A rotary combustion device with shaft power and thrust coupled output, characterized in that: It comprises a front hollow shaft (1), an inclined nozzle (2), a quick-plug ignition nozzle (3), a combustion chamber (4) and a rear hollow shaft (5); The front end hollow shaft (1) and the rear end hollow shaft (5) are respectively located at two ends of the combustion chamber (4), and the front end hollow shaft (1), the rear end hollow shaft (5) and the combustion chamber (4) are coaxial; one end of the front end hollow shaft (1) extends into the combustion chamber (4), and a plurality of nozzles (1-3) are evenly arranged in the circumferential direction of a section of the front end hollow shaft (1) extending into the combustion chamber (4); a baffle (1-4) for blocking the internal chamber of the front end hollow shaft (1) is provided at the end of the front end hollow shaft (1) extending into the combustion chamber (4); The front hollow shaft (1) is used for introducing fuel, and the rear hollow shaft (5) is used for introducing air; A plurality of the inclined nozzles (2) are evenly distributed on the combustion chamber (4) along the circumferential direction; The quick-plug ignition nozzle (3) is also fixedly connected to the outer periphery of the combustion chamber (4).

2. The rotary combustion device with shaft power and thrust coupled output according to claim 1, characterized in that: The front hollow shaft (1), the baffles (1-4) and the combustion chamber (4) are integrally formed by means of additive manufacturing technology.

3. The rotary combustion device with shaft power and thrust coupled output according to claim 1, characterized in that: There are three inclined nozzles (2), which are evenly arranged on the end surface of the combustion chamber (4) close to the front hollow shaft (1).

4. The rotary combustion device with shaft power and thrust coupled output according to claim 1, characterized in that: There are two quick-plug ignition nozzles (3), which are symmetrically arranged on the outer periphery of the combustion chamber (4).

5. The rotary combustion device with shaft power and thrust coupled output according to claim 1, characterized in that: The front hollow shaft (1) and the rear hollow shaft (5) are both stepped shafts with multiple shoulders.

Images