LU501304B1

LU501304B1 - A Hybrid Combined Power System

Info

Publication number: LU501304B1
Application number: LU501304A
Authority: LU
Inventors: Yan Liu
Original assignee: Yan Liu
Priority date: 2022-01-21
Filing date: 2022-01-21
Publication date: 2022-07-21

Abstract

The invention discloses a hybrid combined power system, comprising a motor, one end of the motor is connected to the battery through a transmission line, the other end is connected with a first compressor through a first clutch, the other end of the first compressor is coaxially installed with a second compressor, one end of the second compressor is connected to one end of a steam turbine through the second clutch, the other end of the steam turbine is provided with a third compressor. Compared with the prior art, the invention has the following advantages: referring to the related technologies of "a high-efficiency combined hybrid power system" and "an energy conversion system", a steam generator is installed outside the combustion chambers of the rocket power mechanism and the ramjet engine mechanism, collecting the radiant heat of the combustion chambers of the rocket engine and the ramjet engine, driving the steam turbine to do work, and driving the fuel pump, the oxidant pump and the compressors to work, which can improve the specific impulse of the rocket engine, increase the payload, collect and convert a variety of energy, and jointly supply energy for the rocket, improving the efficiency of energy conversion.

Description

BL-5404 LU501304 A Hybrid Combined Power System Technical Field

[0001] The invention relates to the field of rocket power, in particular to a hybrid combined power system. Background

[0002] The trans-atmospheric aircraft is an important tool for human to explore space, the aircraft needs to get rid of the earth's gravity and atmospheric air resistance when 1t rushes out of the atmosphere, the key technologies are power system and thermal protection.

[0003] The rocket is an aircraft that is propelled forward by the reaction force generated by the rocket engine jetting the working medium. It carries all the propellants by itself and does not rely on the external working medium to generate thrust, it can fly in the dense atmosphere or outside the dense atmosphere, it is a carrier for space flight, rockets are divided into sounding rockets and launch rockets according to their uses.

[0004] The existing rocket power system is single in design and only uses fuel as the main power, which makes the existing rocket thrust and work efficiency not high, therefore, it is imperative to design a hybrid combined power system. Summary of the invention

[0005] The technical problem to be solved by the invention is that most of the existing rocket engines obtain thrust by discharging high-temperature and high-speed gas, the solid or liquid propellant is composed of oxidant and fuel, which are burned at high pressure of 10-200 bar in the combustion chamber to generate gas, the cost is high and the energy conversion efficiency is low, resulting in insufficient rocket thrust and prone to safety accidents.

[0006] To solve the above technical problems, the invention provides the following technical scheme: a hybrid combined power system, comprising a motor, one end of the motor is connected to the battery through a transmission line, the other end is connected with a first compressor through a first clutch, the other end of the first compressor is coaxially installed with a second compressor, one end of the second compressor is connected to one end of a steam turbine through the second clutch, the other end of the steam turbine is provided with a third 1

BL-5404 LU501304 compressor;

[0007] one side of the first compressor is connected with a fuel tank through a fuel delivery pipe, the other side is fixed to the first fuel injector of the steam generator through the fuel delivery pipe connected to the three-way valve assembly;

[0008] one side of the second compressor is connected with the oxidant tank through an oxidant delivery pipe, and the other side is fixed to the second fuel injector of the steam generator through the oxidant delivery pipe connected with the three-way valve assembly;

[0009] one side of the steam turbine is connected to a valve port of the three-way valve assembly through the supercritical working medium delivery pipe, the remaining two valve ports of the three-way valve assembly are respectively connected to one end of the steam generator and the ramjet engine mechanism through the supercritical working medium delivery pipe;

[0010] the other side of the steam turbine is connected to one end of the third compressor through the supercritical working medium delivery pipe, and the other end of the third compressor is connected to the steam generator through the supercritical working medium delivery pipe connected to the three-way valve assembly;

[0011] one end of the valve port of the three-way valve assembly connected to the fuel delivery pipe is connected to the interface of one end of the ramjet engine mechanism through the fuel delivery pipe, and the interface of the other end is connected to the oxidant tank through the oxidant delivery pipe connected to the three-way valve assembly.

[0012] Compared with the prior art, the invention has the following advantages: referring to the related technologies of "a high-efficiency combined hybrid power system" and "an energy conversion system", a steam generator is installed outside the combustion chambers of the rocket power mechanism and the ramjet engine mechanism, collecting the radiant heat of the combustion chambers of the rocket engine and the ramjet engine, driving the steam turbine to do work, and driving the fuel pump, the oxidant pump and the compressors to work, which can improve the specific impulse of the rocket engine, increase the payload, collect and convert a variety of energy, and jointly supply energy for the rocket, improving the efficiency of energy conversion.

[0013] As an improvement, the three-way valve assembly connecting the third compressor and the steam generator, the remaining one valve port of the three-way valve assembly is connected 2

BL-5404 to the ramjet engine mechanism through the supercritical working medium delivery pipe. LUS01304

[0014] As an improvement, one end inside the steam generator is provided with a rocket engine inlet, one side of the rocket engine inlet is connected with the rocket engine tail nozzle through the rocket engine combustion chamber.

[0015] As an improvement, one end of the ramjet engine mechanism is provided with a ramjet engine inlet, and one side of the ramjet engine inlet is connected to the ramjet engine tail nozzle through the ramjet engine combustion chamber.

[0016] As an improvement, the outer wall of the ramjet engine combustion chamber is provided with a ramjet-steam combined power heat conversion wall.

[0017] As an improvement, one end of the supercritical working medium delivery pipe is connected with a desuperheater.

Brief Description of the drawing

[0018] FIG. 1 is a schematic diagram of a hybrid combined power system.

[0019] FIG. 2 is a schematic diagram of the embodiment.

[0020] FIG. 3 is a schematic diagram of the position of the carrier and sub-aircraft of the trans- atmospheric aircraft in the embodiment.

[0021] FIG. 4 is the connection diagram of the fairing-shaped steam turbine power generation system of the embodiment.

[0022] As shown in the figures, 1 refers to the motor, 2 refers to the first clutch, 3 refers to the first compressor, 4 refers to the steam turbine, 5 refers to the first fuel injector, 6 refers to the steam generator, 7 refers to the three-way valve assembly, 8 refers to the rocket engine inlet, 9 refers to the rocket engine combustion chamber, 10 refers to the rocket engine tail nozzle, 11 refers to the ramjet engine inlet, 12 refers to the ramjet engine combustion chamber, 13 refers to the ramjet engine tail nozzle, 14 refers to the fuel tank, 15 refers to the oxidant tank, 16 refers to the desuperheater, 17 refers to the rotating shaft, 18 refers to the supercritical working medium delivery pipe, 19 refers to the gas turbine compressor, 20 refers to the gas turbine combustion chamber, 21 refers to the gas turbine high-pressure turbine, 22 refers to the gas- steam combined power heat conversion wall, 23 refers to the ramjet-steam combined power heat conversion wall, 24 refers to the rocket-steam combined power heat conversion wall, 25 3

BL-5404 refers to the carrier, 26 refers to the sub-aircraft, 27 refers to the fairing-shaped steam turbine 7507504 power generation system, 28 refers to the rocket-steam combined power system, 29 refers to the ramjet-steam combined power system, 30 refers to the battery, 31 refers to the transmission line, 32 refers to the second compressor, 33 refers to the second clutch, 34 refers to the third compressor, 35 refers to the second fuel injector, 36 refers to the fairing-shaped steam generator. Description of Embodiments

[0023] The invention is further explained in combination with the attached drawings.

[0024] When the invention is specifically implemented, a hybrid combined power system, comprising a motor 1, one end of the motor 1 is connected to the battery 30 through a transmission line 31, the other end is connected with a first compressor 3 through a first clutch 2, the other end of the first compressor 3 is coaxially installed with a second compressor 32, one end of the second compressor 32 is connected to one end of a steam turbine 4 through the second clutch 33, the other end of the steam turbine 4 is provided with a third compressor 34;

[0025] one side of the first compressor 3 is connected with a fuel tank 14 through a fuel delivery pipe, the other side is fixed to the first fuel injector 5 of the steam generator 6 through the fuel delivery pipe connected to the three-way valve assembly 7;

[0026] one side of the second compressor 32 is connected with the oxidant tank 15 through an oxidant delivery pipe, and the other side is fixed to the second fuel injector 35 of the steam generator 6 through the oxidant delivery pipe connected with the three-way valve assembly 7;

[0027] one side of the steam turbine 4 is connected to a valve port of the three-way valve assembly 7 through the supercritical working medium delivery pipe 18, the remaining two valve ports of the three-way valve assembly 7 are respectively connected to one end of the steam generator 6 and the ramjet engine mechanism through the supercritical working medium delivery pipe 18;

[0028] the other side of the steam turbine 4 is connected to one end of the third compressor 34 through the supercritical working medium delivery pipe 18, and the other end of the third compressor 34 is connected to the steam generator 6 through the supercritical working medium delivery pipe 18 connected to the three-way valve assembly 7;

[0029] one end of the valve port of the three-way valve assembly 7 connected to the fuel 4

BL-5404 delivery pipe is connected to the interface of one end of the ramjet engine mechanism through 7507504 the fuel delivery pipe, and the interface of the other end is connected to the oxidant tank 15 through the oxidant delivery pipe connected to the three-way valve assembly 7.

[0030] the three-way valve assembly 7 connecting the third compressor 34 and the steam generator 6, the remaining one valve port of the three-way valve assembly is connected to the ramjet engine mechanism through the supercritical working medium delivery pipe 18.

[0031] One end inside the steam generator 6 is provided with a rocket engine inlet 8, one side of the rocket engine inlet 8 is connected with the rocket engine tail nozzle 10 through the rocket engine combustion chamber 9.

[0032] One end of the ramjet engine mechanism is provided with a ramjet engine inlet 11, and one side of the ramjet engine inlet 11 is connected to the ramjet engine tail nozzle 13 through the ramjet engine combustion chamber 12.

[0033] The outer wall of the ramjet engine combustion chamber 12 is provided with a ramjet- steam combined power heat conversion wall 23.

[0034] One end of the supercritical working medium delivery pipe 18 is connected with a desuperheater 16.

[0035] The working principle of the invention: the rocket engine simply uses the steam generator to collect the radiant heat of the combustion chamber to drive the steam turbine, in order to absorb more heat, heat exchange tubes or hollow heat exchange fins can be installed in the combustion chamber to increase the heat exchange area.

[0036] Embodiment:

[0037] one side of the motor 1 is connected to the battery 30 through the transmission line 31, and the other side is connected to the steam generator 6 through the rotating shaft 17, the rotating shaft 17 is sequentially installed with the first clutch 2, the first compressor 3, the second compressor 32 and the second clutch 33, and the third compressor 34 is coaxially installed on the other side of the second clutch 33;

[0038] one end of the first compressor 3 is connected to the fuel tank 14 through the fuel delivery pipe, and the other end is connected to a valve port of the three-way valve assembly 7, the remaining two valve ports of the three-way valve assembly 7 are respectively connected to the first fuel injector 5 of the steam generator 6 and the interface of one end of the ramjet engine

BL-5404 mechanism through the fuel delivery pipes; 7507504

[0039] one end of the second compressor 32 is connected to the oxidant tank 15 through the oxidant delivery pipe, and the other end is connected to a valve port of the three-way valve assembly 7, the remaining two valve ports of the three-way valve assembly 7 are respectively connected to the second fuel injector 35 of the steam generator 6 and the interface of the other end of the ramjet engine mechanism through the oxidant delivery pipes;

[0040] one side of the steam turbine is connected with the three-way valve assembly 7 through a supercritical working medium delivery pipe 18, the remaining two valve ports of the three- way valve assembly 7 are respectively connected to the steam generator 6 and the ramjet engine mechanism through the supercritical working medium delivery pipes 18; the other side is connected to the third compressor 34 through the supercritical working medium delivery pipe 18, and the other end of the third compressor 34 is connected to a valve port of the three-way valve assembly 7, the remaining two valve ports of the three-way valve assembly 7 are respectively connected to the steam generator 6 and the ramjet engine mechanism through the supercritical working medium delivery pipes 18.

[0041] One end of the steam generator 6 is provided with a gas turbine combustion chamber 20, a gas turbine compressor 19 is fixed in the gas turbine combustion chamber 20 through the rotating shaft 17, a gas turbine high-pressure turbine 21 is coaxially installed on one side of the gas turbine compressor 19, one side of the gas turbine combustion chamber 20 is connected to the rocket engine combustion chamber 9 through the rocket engine inlet 8, one side of the rocket engine combustion chamber 9 is provided with the rocket engine tail nozzle 10, a gas-steam combined power heat conversion wall 22 is installed on the outer wall of the rocket engine inlet

8.

[0042] Distinguishing points of the embodiment

[0043] the ramjet engine mechanism is provided with a ramjet engine inlet 11, and one side of the ramjet engine inlet 11 is connected to the ramjet engine tail nozzle 13 through the ramjet engine combustion chamber 12, the outer wall of the ramjet engine combustion chamber 12 is provided with a ramjet-steam combined power heat conversion wall 23.

[0044] One end of the supercritical working medium delivery pipe 18 is connected with a desuperheater 16.

6

BL-5404

[0045] Compared with the original design, the embodiment is also provided with a fairing- LUS01304 shaped steam turbine power generation system 27, the fairing-shaped steam turbine power generation system 27 is respectively installed on the front end of the carrier 25 and the sub- aircraft 26, the fairing-shaped steam turbine power generation system 27 comprises a fairing- shaped steam generator 36, both ends of the fairing-shaped steam generator 36 are connected to the steam turbine 4 through the supercritical working medium delivery pipes 18, a motor 1 is fixed on one side of the steam turbine 4 through a rotating shaft, the motor 1 is connected with a battery 30 through a transmission line 31, a desuperheater 16 is installed on the supercritical working medium delivery pipe 18.

[0046] In the embodiment, the steam generator collects the radiant heat of the combustion chambers of the gas turbine and the rocket engine, driving the steam turbine and the gas turbine together to do work, and driving the fuel tank, the oxidant tank and the compressors to work.

[0047] The fairing-shaped steam generator power generation system, comprising the fairing- shaped steam generator, the supercritical working medium delivery pipe, the steam turbine, the motor, the rotating shaft, the transmission line and the battery, the fairing-shaped steam generator power generation system is used to collect the frictional heat at the front end of the aircraft for power generation, and the electricity generated can be used to do work through the motor.

[0048] Combining rocket engine-steam turbine combined power and ramjet engine-steam turbine combined power to form the power system of the carrier, the sub-aircraft adopts the rocket engine-steam turbine combined power, the carrier first starts the rocket engine-steam turbine combined power, when the aircraft reaches the starting speed of the ramjet engine, the ramjet engine-steam turbine combined power starts, the rocket engine-steam turbine combined power closes, when the ramjet engine flies at high speed, the engine is prone to overheating due to the increased static pressure in the intake and frictional heat, before the ramjet engine reaches the heat-resistant limit, the carrier releases the sub-aircraft, and the sub-aircraft starts the rocket engine-steam turbine combined power to continue flying, rushing out of the atmosphere.

[0049] The steam cycle of the invention adopts supercritical Brayton cycle.

[0050] In addition, the terms "first" and "second" are only used for descriptive purposes, and should not be understood as indicating or implying relative importance or implying the number 7

BL-5404 of indicated technical features. Therefore, the features defined with "first" or "second" may LUS01304 expressly or implicitly include one or more of the features, and in the description of the invention, the meaning of "multiple" is two or more, unless otherwise expressly limited.

[0051] In the invention, unless otherwise expressly specified and limited, the terms "installation", "connected", "connection", "fixed" and so on should be understood in a broad sense, for example, it may be a fixed connection or a detachable connection or integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, and it can be the internal connection between the two components. For those skilled in the art, the specific meanings of the above terms in the invention can be understood according to specific situations.

[0052] In the invention, unless otherwise expressly specified and limited, a first feature "on" or "under" a second feature may include direct contact between the first and second feature, or may include contact between the first and second feature not directly but through the other feature between them. Moreover, the first feature "on", "over" and "above" the second feature include the first feature directly above and obliquely above the second feature, or simply means that the level of the first feature is higher than the level of the second feature. The first feature "under", "below" and "underneath" the second feature include the first feature directly below and obliquely below the second feature, or simply means that the level of the first feature is lower than the level of the second feature.

[0053] In the description of the specification, the terms "one embodiment," "some embodiments," "example," "specific example," or "some examples", etc., mean the specific features, structures, materials, or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the invention. In this specification, indicative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials or characteristics described may be combined in an appropriate manner in any one or more embodiments or examples.

[0054] Although the embodiments of the invention have been shown and described above, it should be understood that the above embodiments are exemplary and should not be understood as limitations of the invention. Those skilled in the art can make changes, modifications, 8

BL-5404 Le . . SL: . . LU501304 substitutions and alterations to the above embodiments within the scope of the invention without departing from the principles and spirit of the invention. 9

Claims

BL-5404 Claims LU501304

1. Ahybrid combined power system, comprising a motor 1, wherein one end of the motor 1 is connected to the battery 30 through a transmission line 31, the other end is connected with a first compressor 3 through a first clutch 2, the other end of the first compressor 3 is coaxially installed with a second compressor 32, one end of the second compressor 32 is connected to one end of a steam turbine 4 through the second clutch 33, the other end of the steam turbine 4 is provided with a third compressor 34; one side of the first compressor 3 is connected with a fuel tank 14 through a fuel delivery pipe, the other side is fixed to the first fuel injector 5 of the steam generator 6 through the fuel delivery pipe connected to the three-way valve assembly 7; one side of the second compressor 32 is connected with the oxidant tank 15 through an oxidant delivery pipe, and the other side is fixed to the second fuel injector 35 of the steam generator 6 through the oxidant delivery pipe connected with the three-way valve assembly 7; one side of the steam turbine 4 is connected to a valve port of the three-way valve assembly 7 through the supercritical working medium delivery pipe 18, the remaining two valve ports of the three-way valve assembly 7 are respectively connected to one end of the steam generator 6 and the ramjet engine mechanism through the supercritical working medium delivery pipe 18; the other side of the steam turbine 4 is connected to one end of the third compressor 34 through the supercritical working medium delivery pipe 18, and the other end of the third compressor 34 is connected to the steam generator 6 through the supercritical working medium delivery pipe 18 connected to the three-way valve assembly 7; one end of the valve port of the three-way valve assembly 7 connected to the fuel delivery pipe is connected to the interface of one end of the ramjet engine mechanism through the fuel delivery pipe, and the interface of the other end is connected to the oxidant tank 15 through the oxidant delivery pipe connected to the three-way valve assembly 7.

2. A hybrid combined power system according to claim 1, wherein the three-way valve assembly 7 connecting the third compressor 34 and the steam generator 6, the remaining one valve port of the three-way valve assembly is connected to the ramjet engine mechanism through the supercritical working medium delivery pipe 18.

3. A hybrid combined power system according to claim 2, wherein one end inside the

BL-5404 steam generator 6 is provided with a rocket engine inlet 8, one side of the rocket engine inlet 8 LUS01304 is connected with the rocket engine tail nozzle 10 through the rocket engine combustion chamber 9.

4. Ahybrid combined power system according to claim 3, wherein one end of the ramjet engine mechanism is provided with a ramjet engine inlet 11, and one side of the ramjet engine inlet 11 is connected to the ramjet engine tail nozzle 13 through the ramjet engine combustion chamber 12.

5. A hybrid combined power system according to claim 4, wherein the outer wall of the ramjet engine combustion chamber 12 is provided with a ramjet-steam combined power heat conversion wall 23.

6. A hybrid combined power system according to claim 5, wherein one end of the supercritical working medium delivery pipe 18 is connected with a desuperheater 16.

7. A hybrid combined power system with a fairing-shaped steam turbine power generation system, wherein the system comprises a hybrid combined power system according to claim 1, the hybrid combined power system is also provided with a fairing-shaped steam turbine power generation system 27, the fairing-shaped steam turbine power generation system 27 is respectively installed on the front end of the carrier 25 and the sub-aircraft 26, the fairing- shaped steam turbine power generation system 27 comprises a fairing-shaped steam generator 36, both ends of the fairing-shaped steam generator 36 are connected to the steam turbine 4 through the supercritical working medium delivery pipes 18, a motor 1 is fixed on one side of the steam turbine 4 through a rotating shaft, the motor 1 is connected with a battery 30 through a transmission line 31, a desuperheater 16 is installed on the supercritical working medium delivery pipe 18.

11