CN108757182B - air-breathing rocket engine and hypersonic aircraft - Google Patents
air-breathing rocket engine and hypersonic aircraft Download PDFInfo
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- CN108757182B CN108757182B CN201810529464.XA CN201810529464A CN108757182B CN 108757182 B CN108757182 B CN 108757182B CN 201810529464 A CN201810529464 A CN 201810529464A CN 108757182 B CN108757182 B CN 108757182B
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- 238000002485 combustion reaction Methods 0.000 claims abstract description 66
- 239000000446 fuel Substances 0.000 claims abstract description 56
- 239000007789 gas Substances 0.000 claims abstract description 54
- 239000007800 oxidant agent Substances 0.000 claims abstract description 54
- 230000001590 oxidative effect Effects 0.000 claims abstract description 45
- 238000001816 cooling Methods 0.000 claims abstract description 39
- 239000007921 spray Substances 0.000 claims abstract description 9
- 239000000567 combustion gas Substances 0.000 claims abstract description 6
- 239000007788 liquid Substances 0.000 claims description 25
- 239000002826 coolant Substances 0.000 claims description 13
- MHAJPDPJQMAIIY-UHFFFAOYSA-N Hydrogen peroxide Chemical compound OO MHAJPDPJQMAIIY-UHFFFAOYSA-N 0.000 claims description 6
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 6
- PAWQVTBBRAZDMG-UHFFFAOYSA-N 2-(3-bromo-2-fluorophenyl)acetic acid Chemical compound OC(=O)CC1=CC=CC(Br)=C1F PAWQVTBBRAZDMG-UHFFFAOYSA-N 0.000 claims description 3
- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 claims description 3
- 238000004891 communication Methods 0.000 claims description 3
- 239000001257 hydrogen Substances 0.000 claims description 3
- 229910052739 hydrogen Inorganic materials 0.000 claims description 3
- 239000003350 kerosene Substances 0.000 claims description 3
- 239000003949 liquefied natural gas Substances 0.000 claims description 3
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 claims description 2
- 230000029058 respiratory gaseous exchange Effects 0.000 claims 1
- 239000002737 fuel gas Substances 0.000 abstract description 7
- 238000002309 gasification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 239000004215 Carbon black (E152) Substances 0.000 description 1
- 238000010521 absorption reaction Methods 0.000 description 1
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000000354 decomposition reaction Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 229930195733 hydrocarbon Natural products 0.000 description 1
- 150000002430 hydrocarbons Chemical class 0.000 description 1
- 150000002431 hydrogen Chemical class 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 239000001301 oxygen Substances 0.000 description 1
- 229910052760 oxygen Inorganic materials 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
- F02C7/14—Cooling of plants of fluids in the plant, e.g. lubricant or fuel
- F02C7/141—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid
- F02C7/143—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid before or between the compressor stages
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/20—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products
- F02C3/22—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products the fuel or oxidant being gaseous at standard temperature and pressure
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/20—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products
- F02C3/24—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products the fuel or oxidant being liquid at standard temperature and pressure
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
- F02C7/16—Cooling of plants characterised by cooling medium
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
the invention discloses an air-breathing rocket engine and a hypersonic aircraft, which comprises an air inlet channel, a heat exchanger, a gas compressor, a main combustion chamber and a spray pipe which are arranged in sequence, wherein the gas compressor is provided with a turbine for providing driving force for the gas compressor, and the outer wall surfaces of the main combustion chamber and the spray pipe are provided with wall surface cooling channels, and the air-breathing rocket engine further comprises: and the oxidant pump is communicated with the heat exchanger so that the oxidant enters the heat exchanger to cool the air entering from the air inlet channel. The fuel pump is communicated with the wall surface cooling channel so that the fuel enters the wall surface cooling channel to cool the spray pipe and the main combustion chamber. The device also comprises a pre-combustion chamber, so that an oxidant after cooling air and fuel after the cooling jet pipe and the main combustion chamber respectively enter the pre-combustion chamber to be combusted so as to generate rich combustion gas, and an outlet of the pre-combustion chamber faces to the turbine so that the rich combustion gas drives the turbine to do work. The gas-fired boiler also comprises an injector which is used for respectively injecting the air cooled by the heat exchanger and pressurized by the compressor and the rich-fuel gas driving the turbine into the main combustion chamber for mixed combustion.
Description
Technical Field
The invention relates to the field of aircraft engines, in particular to an air-breathing rocket engine. Furthermore, the invention also relates to a hypersonic speed airplane comprising the air-breathing rocket engine.
Background
at present, there are two main classes of engines that find application in the aerospace field: piston engines and gas turbine engines. The application of piston type internal combustion engine in the plane opens a new era of human flight. The advent of gas turbine engines enabled humans to achieve supersonic flight. With the advent of the hypersonic flight era, gas turbine engines face insurmountable technical difficulties, which must also be subverted by new engine technology.
In the future, hypersonic aircrafts can horizontally take off and land and can cruise and fly at hypersonic speed, a power system of the hypersonic aircrafts must have the capability of working in a wide Mach number range (Ma 0-5 +), and the existing gas turbine engine cannot meet the requirement. Because the total temperature of the incoming air flow exceeds 1200K at high supersonic flight speeds (typically greater than 5 times the speed of sound), the high speed rotating fan and compressor blades are difficult to withstand this thermal load and must be cooled. More seriously, the temperature of the air after being compressed by the air compressor is further increased, the temperature of the air entering the combustion chamber is over 2000K according to the calculation of 10 times of pressure ratio, and even if the oil is not injected for combustion, the temperature of the air is close to the temperature resistance limit of the turbine blade material. In fact, the current upper operating limit of gas turbine engines does not exceed mach number 3.
In order to solve the power problem of the hypersonic aircraft, various schemes of air-breathing engines working in wide speed range are provided at home and abroad. The first type is that a medium is adopted to cool an incoming air flow so as to expand the working range of a traditional aeroengine, such as a turbine engine (MIPCCE) with front jet cooling of a compressor, which is proposed by the MSE technology application company in the United states, and a precooling air turbine engine (PCTJ) which is proposed by the research institute of Japanese space and aviation science. Both engines need to carry extra coolant or consume more cryogenic fuel, resulting in low specific impulse performance and poor economy. The second type is to adopt various engine combinations to realize wide-speed-range flight, such as: a turbine-based combined cycle engine (TBCC), a rocket-based combined cycle engine (RBCC). However, when one engine works, the other engine which does not work is dead and heavy, and the requirements of the hypersonic aircraft on weight and volume are difficult to meet. An air turbine rocket engine (ATR) also belongs to a combined engine, but the ATR can not realize hypersonic flight like an aircraft engine due to the adoption of a turbine-compressor. The third category is a full-speed range engine with a new concept, such as: the cooperative air-breathing rocket engine (SABRE) proposed by british reaction engine company not only needs to carry special coolant (which can be recycled and is not consumed), but also needs to use low-temperature fuel and low-temperature oxidant as cold sources, and the working cycle of the engine is very complex, so that the number of components of the engine system is large, and the structure is complex.
In addition to the above-mentioned several schemes of air-breathing engines, a rocket engine can be used as the power of a hypersonic speed airplane, for example, in the X-15 airplane in the sixties of the last century of the United states, a liquid rocket engine is used as the power, but the rocket engine cannot utilize oxygen in the air for combustion, needs to carry a large amount of oxidant, and therefore has low specific impulse. Compared with an air-breathing engine, the aircraft has short range and cannot easily realize horizontal takeoff.
Disclosure of Invention
The invention provides an air-breathing rocket engine and a hypersonic aircraft, and aims to solve the technical problem that the conventional aviation turbofan/turbojet engine cannot realize hypersonic flight.
The technical scheme adopted by the invention is as follows:
The utility model provides an air-breathing rocket engine, is including the intake duct, heat exchanger, compressor, main combustion chamber and the spray tube that set gradually, and the compressor is equipped with the turbine that provides drive power for it, and the outer wall of main combustion chamber and spray tube is equipped with wall cooling channel, and air-breathing rocket engine still includes: the oxidant pump is used for providing liquid oxidant serving as a coolant and the oxidant, and is communicated with the heat exchanger so that the oxidant enters the heat exchanger and cools air entering from the air inlet channel; a fuel pump for supplying a liquid fuel as a fuel and a coolant, the fuel pump being in communication with the wall cooling gallery for admitting the fuel into the wall cooling gallery cooling nozzle and the main combustion chamber; the precombustion chamber is communicated with the heat exchanger and the wall surface cooling channel respectively, so that an oxidant after cooling air and fuel after the cooling spray pipe and the main combustion chamber enter the precombustion chamber respectively to be mixed and combusted to generate rich fuel gas with rich fuel, and the outlet of the precombustion chamber faces the turbine so that the rich fuel gas drives the turbine to do work; and the injector is positioned at the head of the main combustion chamber and is used for respectively injecting the air cooled by the heat exchanger and pressurized by the air compressor and the rich combustion gas driving the turbine into the main combustion chamber for mixed combustion so as to generate thrust.
Further, the air-breathing rocket engine also comprises a first connecting pipe used for communicating the heat exchanger with the pre-combustion chamber and a second connecting pipe used for communicating the wall surface cooling channel with the pre-combustion chamber; the first connecting pipe is used for guiding an oxidant subjected to heat exchange with air through the heat exchanger into the precombustion chamber; the second connecting pipe is used for guiding fuel after the cooling spray pipe in the wall surface cooling channel and the main combustion chamber into the precombustion chamber.
Furthermore, the air-breathing rocket engine also comprises a gas pipeline arranged between the turbine and the injector, wherein the gas inlet of the gas pipeline is connected with the gas outlet of the turbine, the gas outlet of the gas pipeline is connected with the gas inlet of the injector, and the gas pipeline is used for guiding rich-fuel gas which drives the turbine to do work into the injector.
Further, the gas pipeline comprises a ring-shaped flared pipe and a straight pipe connected with the flared pipe; the bell mouth of the bell-mouthed pipe is communicated with the turbine; the air outlet of the straight pipe is connected with the injector.
furthermore, the air-breathing rocket engine also comprises an air pipeline arranged on the periphery of the gas pipeline, an air inlet of the air pipeline is connected with an air outlet of the air compressor, an air outlet of the air pipeline is connected with an air inlet of the injector, and the air pipeline is used for guiding air pressurized by the air compressor into the injector.
Further, the injector comprises a plurality of nozzles which are coaxially arranged, and the plurality of nozzles are used for respectively injecting air and fuel-rich gas into the main combustion chamber to be fully mixed and then combusted.
further, the first motor for driving the oxidant pump to operate is connected to the oxidant pump, and the second motor for driving the fuel pump to operate is connected to the fuel pump.
Furthermore, the air-breathing rocket engine also comprises a generator arranged between the gas compressor and the turbine, and a rotor of the generator and a rotor of the gas compressor are respectively arranged on a rotating shaft of the turbine; the generators are respectively connected with the first motor and the second motor to respectively provide driving electric energy for the first motor and the second motor.
Further, the oxidant is one of liquid oxygen, hydrogen peroxide and ammonium nitrate solution; the fuel is one of kerosene, liquefied natural gas, liquid methane and liquid hydrogen.
According to another aspect of the invention there is also provided a hypersonic aircraft comprising an air-breathing rocket engine as in any one of the preceding claims.
the invention has the following beneficial effects:
Compared with an aero-engine, the liquid oxidant is adopted to cool the incoming air flow, so that the air temperature in front of the air compressor can be greatly reduced, the air compressor can still normally work under the condition of high Mach number, the problem of the upper limit of the flight speed (Ma <3) of the conventional aero-engine is solved by cooling the incoming air flow, the air-breathing rocket engine can work within the wide Mach number range of Ma 0-6, and the hypersonic aircraft can achieve horizontal take-off and landing and hypersonic flight. Compared with a rocket engine, the invention greatly reduces the amount of the oxidant carried by the engine by using air as most of the oxidant, so that the specific impulse of the engine is improved by about 30 percent compared with the rocket engine. Compared with the traditional cooling scheme, the air-breathing rocket engine adopts the liquid oxidant as the coolant to cool the incoming flow, so that extra coolant is not required to be carried, the oxidant cools air and then completely participates in combustion in the precombustion chamber, heat energy is fully utilized, the thrust performance of the engine is not lost, and the thrust performance of the engine is good. The traditional aero-engine adopts a gas compressor to compress incoming air, high-pressure air and fuel are organized and combusted in a combustion chamber, combustion products drive a turbine to do work, the turbine drives the gas compressor to work, and the gas compressor, the combustion chamber and the turbine are mutually coupled. In addition, in the invention, the combustion gas for driving the turbine is generated by the precombustion chamber, so that the state of the turbine is easier to control and is not influenced by the flying state of the engine.
in addition to the objects, features and advantages described above, other objects, features and advantages of the present invention are also provided. The present invention will be described in further detail below with reference to the drawings.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, illustrate embodiments of the invention and, together with the description, serve to explain the invention and not to limit the invention. In the drawings:
FIG. 1 is a schematic view of an air-breathing rocket engine according to a preferred embodiment of the present invention.
description of the figures
10. An air inlet channel; 20. a heat exchanger; 30. a compressor; 40. a main combustion chamber; 50. a nozzle; 60. a turbine; 70. an oxidant pump; 80. a fuel pump; 90. a precombustion chamber; 110. an injector; 120. a first connecting pipe; 130. a second connecting pipe; 140. a gas pipeline; 150. an air duct; 160. a first motor; 170. a second motor; 180. an electric generator.
Detailed Description
The embodiments of the invention will be described in detail below with reference to the drawings, but the invention can be implemented in many different ways as defined and covered by the claims.
Referring to fig. 1, a preferred embodiment of the present invention provides an air-breathing rocket engine, which includes an air intake duct 10, a heat exchanger 20, a compressor 30, a main combustion chamber 40, and a nozzle 50, which are sequentially disposed, wherein the compressor 30 is provided with a turbine 60 for providing a driving force thereto, wall-cooling passages are provided on outer wall surfaces of the main combustion chamber 40 and the nozzle 50, and the air-breathing rocket engine further includes: and an oxidizer pump 70 for supplying liquid oxidizer as a coolant and an oxidizer, wherein the oxidizer pump 70 is communicated with the heat exchanger 20 to cool the air introduced from the inlet duct 10 by the oxidizer entering the heat exchanger 20. A fuel pump 80 is also included for supplying a liquid fuel as a fuel and coolant, the fuel pump 80 communicating with the wall cooling gallery to allow the fuel to enter the wall cooling gallery cooling nozzle 50 and the main combustion chamber 40. The pre-combustion chamber 90 is further included, and is respectively communicated with the heat exchanger 20 and the wall surface cooling channel, so that the oxidant after cooling air and the fuel after cooling the nozzle 50 and the main combustion chamber 40 respectively enter the pre-combustion chamber 90 to be mixed and combusted to generate fuel-rich fuel gas, and an outlet of the pre-combustion chamber 90 faces the turbine 60, so that the fuel-rich fuel gas drives the turbine 60 to do work. The combustor also comprises an injector 110 which is positioned at the head of the main combustion chamber 40 and is used for respectively injecting air cooled by the heat exchanger 20 and pressurized by the compressor 30 and fuel-rich gas driving the turbine 60 into the main combustion chamber 40 for mixed combustion to generate thrust.
When the air-breathing rocket engine of the invention works, the liquid oxidant is pressurized by the oxidant pump 70 and then enters the heat exchanger 20, and in the stages of takeoff/landing and low-speed flight, when the temperature of the incoming air is low, the oxidant absorbs little heat in the heat exchanger 20 and does not have phase change, so the oxidant still enters the precombustion chamber 90 in a liquid state. Along with the increase of the flying speed, the temperature of the incoming air gradually rises, the heat absorption capacity of the liquid oxidant in the heat exchanger 20 increases, when the flying speed reaches hypersonic speed flying, the liquid oxidant undergoes phase change gasification or gasification decomposition after the temperature rises, and then enters the precombustion chamber 90 in a gas phase to participate in combustion. After being pressurized by the fuel pump 80, the liquid fuel enters the nozzle 50 and the wall cooling passage of the main combustion chamber 40, absorbs heat to be heated and gasified or gasified and cracked in the passage, and then enters the pre-combustion chamber 90 in a gas phase to participate in combustion. The pre-combustion chamber 90 is ignited to work, the fuel and the oxidant are combusted to generate fuel-rich gas, the fuel-rich gas drives the turbine 60 to power the compressor 30, and the fuel-rich gas after driving the turbine 60 enters the injector 110 to be injected into the main combustion chamber 40. After being diffused by the air inlet 10, the air enters the injector 110 after being cooled by the heat exchanger 20 and pressurized by the compressor 30 to be injected into the main combustion chamber 40, and is subjected to afterburning with the rich fuel gas after driving the turbine 60, and the afterburning product is discharged through the nozzle 50 to generate thrust.
Compared with an aero-engine, the liquid oxidizer is adopted to cool the incoming air flow, so that the air temperature in front of the air compressor 30 can be greatly reduced, the air compressor 30 can still normally work under the condition of high Mach number, the problem of the upper limit of the flight speed (Ma <3) of the conventional aero-engine is solved by cooling the incoming air flow, the air-breathing rocket engine can work within the wide Mach number range of Ma 0-6, and the hypersonic aircraft can achieve horizontal take-off and landing and hypersonic flight. Compared with a rocket engine, the invention greatly reduces the amount of the oxidant carried by the engine by using air as most of the oxidant, so that the specific impulse of the engine is improved by about 30 percent compared with the rocket engine. Compared with the traditional cooling scheme, the liquid oxidant used as the oxidant in the air-breathing rocket engine is used as the coolant to cool incoming flow, so that extra coolant does not need to be carried, the oxidant cools air and then completely participates in combustion in the precombustion chamber, the thrust performance of the engine is not lost, and the thrust performance of the engine is good. The traditional aero-engine adopts a gas compressor to compress incoming air, high-pressure air and fuel are organized and combusted in a combustion chamber, combustion products drive a turbine to do work, the turbine drives the gas compressor to work, and the gas compressor, the combustion chamber and the turbine are mutually coupled. In addition, in the invention, the combustion gas for driving the turbine is generated by the precombustion chamber, so that the state of the turbine is easier to control and is not influenced by the flying state of the engine.
optionally, as shown in FIG. 1, the air-breathing rocket engine further comprises a first connecting pipe 120 for communicating the heat exchanger 20 and the pre-chamber 90, and a second connecting pipe 130 for communicating the wall cooling passage and the pre-chamber 90. First connecting tube 120 is configured to direct oxidant after heat exchange with air via heat exchanger 20 into prechamber 90. The second connecting tube 130 is used to direct fuel from the cooling nozzle 50 and the main combustion chamber 40 in the wall cooling gallery to the prechamber 90.
Optionally, as shown in fig. 1, the air-breathing rocket engine further includes a gas duct 140 disposed between the turbine 60 and the injector 110, an air inlet of the gas duct 140 is connected to an air outlet of the turbine 60, an air outlet of the gas duct 140 is connected to an air inlet of the injector 110, and the gas duct 140 is used for introducing the rich-burn gas, which drives the turbine 60 to do work, into the injector 110. In this alternative embodiment, the gas conduit 140 includes a flare in the shape of a ring, and a straight pipe connected to the flare. The bell mouth of the bell-mouthed pipe is communicated with the turbine. The outlet of the straight tube is connected to the injector 110. Optionally, as shown in fig. 1, the air-breathing rocket engine further includes an air duct 150 disposed at an outer periphery of the gas duct 140, an air inlet of the air duct 150 is connected to an air outlet of the compressor 30, an air outlet of the air duct 150 is connected to an air inlet of the injector 110, and the air duct 150 is configured to guide air pressurized by the compressor 30 into the injector 110.
Preferably, as shown in FIG. 1, the injector 110 includes a plurality of coaxially disposed nozzles for injecting air and fuel-rich gas into the main combustion chamber 40, respectively, for thorough mixing and combustion. The present invention adopts the injector 110 to inject the high pressure air and the fuel-rich gas into the main combustion chamber 40, and the injector 110 is composed of a plurality of coaxially arranged nozzles, so that the air and the fuel-rich gas can be fully mixed, and the combustion efficiency can be further improved.
Alternatively, as shown in fig. 1, the oxidant pump 70 is connected to a first motor 160 for driving the operation thereof, and the fuel pump 80 is connected to a second motor 170 for driving the operation thereof. Further, the air-breathing rocket engine further comprises a generator 180 arranged between the compressor 30 and the turbine 60, and a rotor of the generator 180 and a rotor of the compressor 30 are respectively arranged on a rotating shaft of the turbine 60. The generator 180 is connected to the first motor 160 and the second motor 170, respectively, to supply driving power to the first motor 160 and the second motor 170, respectively. In the invention, the rotor of the generator 180 and the rotor of the compressor 30 are respectively arranged on the rotating shaft of the turbine 60, so that the compressor 30, the turbine 60 and the generator 180 are integrated, the mode of driving accessories (such as a generator) through transverse gear shaft transmission in the conventional aircraft engine is avoided, and the structure of the engine is simple and compact.
Alternatively, as shown in fig. 1, in the present invention, the aircraft uses its own liquid oxidizer (liquid oxygen, hydrogen peroxide, ammonium nitrate solution, etc.) as the oxidizer, and uses the heat sink of the liquid oxidizer to cool the air after the air inlet 10 through the heat exchanger 20. Liquid hydrocarbon fuels (kerosene, liquefied natural gas, liquid methane, liquid hydrogen, etc.) are used as fuels and as coolants for the main combustion chamber 40 and the lance 50 of the engine.
according to another aspect of the invention, there is also provided a hypersonic aircraft comprising an air-breathing rocket engine of the above-described embodiments. Experiments prove that the hypersonic aircraft can work in a wide Mach number range (Ma 0-6), and the problem that the conventional aviation turbofan/turbojet engine cannot realize hypersonic flight can be solved.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. The utility model provides an air-breathing rocket engine, is including air inlet (10), heat exchanger (20), compressor (30), main combustion chamber (40) and spray tube (50) that set gradually, compressor (30) are equipped with turbine (60) for it provides drive power, main combustion chamber (40) with the outer wall of spray tube (50) is equipped with wall cooling channel, its characterized in that, air-breathing rocket engine still includes:
An oxidant pump (70) for supplying an oxidant in a liquid state as a coolant and an oxidant, the oxidant pump (70) being in communication with the heat exchanger (20) to cause the oxidant to enter the heat exchanger (20) and cool air entering from the intake duct (10);
a fuel pump (80) for providing a liquid fuel as a fuel and a coolant, said fuel pump (80) communicating with said wall cooling channel such that said fuel enters said wall cooling channel to cool said lance (50) and said main combustion chamber (40);
A prechamber (90) in communication with the heat exchanger (20) and the wall cooling channel, respectively, for the oxidant after cooling air and the fuel after cooling the nozzle (50) and the main combustion chamber (40) to enter the prechamber (90) for mixed combustion to generate fuel-rich gas, an outlet of the prechamber (90) facing the turbine (60) such that the fuel-rich gas drives the turbine (60) to do work;
And the injector (110) is positioned at the head of the main combustion chamber (40) and is used for respectively injecting the air cooled by the heat exchanger (20) and pressurized by the compressor (30) and the fuel-rich gas driving the turbine (60) into the main combustion chamber (40) for mixed combustion to generate thrust.
2. An air-breathing rocket engine according to claim 1,
the air-breathing rocket engine further comprising a first connecting pipe (120) for communicating the heat exchanger (20) and the pre-chamber (90) and a second connecting pipe (130) for communicating the wall cooling channel and the pre-chamber (90);
The first connecting pipe (120) is used for introducing an oxidant which exchanges heat with air through the heat exchanger (20) into the prechamber (90);
The second connecting pipe (130) is used for guiding the fuel cooled in the wall cooling channel by the nozzle (50) and the main combustion chamber (40) into the precombustion chamber (90).
3. An air-breathing rocket engine according to claim 1,
The air-breathing rocket engine further comprises a gas pipeline (140) arranged between the turbine (60) and the injector (110), wherein an air inlet of the gas pipeline (140) is connected with an air outlet of the turbine (60), an air outlet of the gas pipeline (140) is connected with an air inlet of the injector (110), and the gas pipeline (140) is used for guiding rich-combustion gas which drives the turbine (60) to do work into the injector (110).
4. An air-breathing rocket engine according to claim 3,
The gas pipeline (140) comprises an annular flared pipe and a straight pipe connected with the flared pipe;
The bell mouth of the bell pipe is communicated with the turbine (60);
The air outlet of the straight pipe is connected with the injector (110).
5. an air-breathing rocket engine according to claim 3,
The air-breathing rocket engine further comprises an air pipeline (150) arranged on the periphery of the gas pipeline (140), an air inlet of the air pipeline (150) is connected with an air outlet of the compressor (30), an air outlet of the air pipeline (150) is connected with an air inlet of the injector (110), and the air pipeline (150) is used for guiding air pressurized by the compressor (30) into the injector (110).
6. an air-breathing rocket engine according to claim 1,
The injector (110) comprises a plurality of nozzles which are coaxially arranged and are used for respectively injecting air and fuel-rich gas into the main combustion chamber (40) to be fully mixed and then combusted.
7. an air-breathing rocket engine according to claim 1,
the oxidant pump (70) is connected with a first motor (160) for driving the oxidant pump to move, and the fuel pump (80) is connected with a second motor (170) for driving the fuel pump to move.
8. An air-breathing rocket engine according to claim 7,
The air-breathing rocket engine also comprises a generator (180) arranged between the compressor (30) and the turbine (60), and a rotor of the generator (180) and a rotor of the compressor (30) are respectively arranged on a rotating shaft of the turbine (60);
The generators (180) are respectively connected with the first motor (160) and the second motor (170) to respectively provide driving electric energy for the first motor (160) and the second motor (170).
9. an air-breathing rocket engine according to claim 1,
The oxidant is one of liquid oxygen, hydrogen peroxide and ammonium nitrate solution;
The fuel is one of kerosene, liquefied natural gas, liquid methane and liquid hydrogen.
10. a hypersonic aircraft comprising an air breathing rocket motor according to any one of claims 1 to 9.
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| CN109736971B (en) * | 2018-12-13 | 2021-05-04 | 西安航天动力研究所 | Electric pump pressure type liquid rocket engine |
| CN109733634B (en) * | 2019-01-08 | 2020-11-24 | 厦门大学 | Design method of three-dimensional inward-turning four-channel hypersonic combined air inlet channel |
| CN109826721A (en) * | 2019-04-03 | 2019-05-31 | 中南大学 | It is a kind of that the device and its engine of air and fuel-rich combustion gas are provided |
| CN110700966A (en) * | 2019-09-18 | 2020-01-17 | 北京星际荣耀空间科技有限公司 | Rocket engine heat exchanger and aerospace vehicle |
| CN112431675B (en) * | 2020-11-24 | 2022-08-02 | 西北工业大学 | Combined scramjet engine cooling circulation system |
| CN113738514B (en) * | 2021-08-12 | 2022-07-12 | 南京航空航天大学 | Multi-mode combined power cycle system and method for precooling/supporting combustion by using N2O |
| CN115450793B (en) * | 2022-09-06 | 2024-07-26 | 中国人民解放军国防科技大学 | Air suction type ramjet engine adopting oil-water mixed combustion |
| CN115822815B (en) * | 2022-11-29 | 2024-09-17 | 中国科学院力学研究所 | Air suction type rocket pintle injector and injection method thereof |
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