CN111075605A - Hybrid combined power system - Google Patents

Hybrid combined power system Download PDF

Info

Publication number
CN111075605A
CN111075605A CN201911324281.5A CN201911324281A CN111075605A CN 111075605 A CN111075605 A CN 111075605A CN 201911324281 A CN201911324281 A CN 201911324281A CN 111075605 A CN111075605 A CN 111075605A
Authority
CN
China
Prior art keywords
compressor
ramjet
conveying pipe
way valve
valve assembly
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
CN201911324281.5A
Other languages
Chinese (zh)
Inventor
刘彦
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Individual
Original Assignee
Individual
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Individual filed Critical Individual
Priority to CN201911324281.5A priority Critical patent/CN111075605A/en
Publication of CN111075605A publication Critical patent/CN111075605A/en
Withdrawn legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
    • F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
    • F02K7/18—Composite ram-jet/rocket engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/44—Feeding propellants
    • F02K9/46—Feeding propellants using pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/44—Feeding propellants
    • F02K9/56—Control
    • F02K9/58—Propellant feed valves
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)

Abstract

The invention discloses a hybrid combined power system which comprises a motor, wherein one end of the motor is connected with a battery through a power line, the other end of the motor is connected with a first compressor through a clutch, the other end of the first compressor is coaxially provided with a second compressor, one end of the second compressor is connected with one end of a steam turbine through the second clutch, and the other end of the steam turbine is provided with a third compressor. Compared with the prior art, the invention has the advantages that: a steam generator is arranged outside a combustion chamber of a rocket power mechanism and a ramjet mechanism, collects radiant heat of the combustion chamber of the rocket engine and the ramjet mechanism, drives a steam turbine to do work, drives a fuel pump, an oxidant pump and a compressor to work, can improve the specific impulse resistance of the rocket engine, increase effective load, collect and convert various energies, jointly supplies energy to the rocket, and improves the energy conversion efficiency.

Description

Hybrid combined power system
Technical Field
The invention relates to the field of rocket power, in particular to a hybrid combined power system.
Background
The air vehicle crossing the atmospheric layer is an important tool for people to explore the space, the air vehicle rushes out of the atmospheric layer needs to get rid of the earth attraction and the atmospheric air resistance, and the key technology is a power system and thermal protection.
The rocket is an aircraft propelled forward by the reaction force generated by the working medium injected by a rocket engine. The aircraft carries all propellants, does not depend on an external working medium to generate thrust, can fly in a dense atmosphere and also outside the dense atmosphere, is a carrier for realizing space flight, and is divided into a sounding rocket and a carrier rocket according to purposes.
The existing rocket power system is single in design, and only uses fuel as main power, so that the existing rocket has low thrust and working efficiency, and therefore, the design of a hybrid combined power system is imperative.
Disclosure of Invention
The invention aims to solve the technical problems that most of the existing rocket engines obtain thrust by discharging high-temperature and high-speed fuel gas, solid or liquid propellant consists of oxidant and fuel and is combusted in a combustion chamber at high pressure of 10-200bar to generate fuel gas, the cost is high, the energy conversion efficiency is not high, the rocket thrust is insufficient, and safety accidents are easy to occur.
In order to solve the technical problems, the technical scheme provided by the invention is as follows: a hybrid combined power system comprises a motor, wherein one end of the motor is connected with a battery through a power line, the other end of the motor is connected with a first compressor through a clutch, the other end of the first compressor is coaxially provided with a second compressor, one end of the second compressor is connected with one end of a steam turbine through the second clutch, and the other end of the steam turbine is provided with a third compressor;
one side of the compressor is connected with a fuel tank through a fuel delivery pipe, and the other side of the compressor is fixed on a fuel injector I of the steam generator through the fuel delivery pipe connected with a three-way valve assembly;
one side of the compressor II is connected with an oxidant box through an oxidant conveying pipe, and the other side of the compressor II is fixed on a fuel injector II of the steam generator through an oxidant conveying pipe connected with a three-way valve assembly;
one side of the steam turbine is connected to one valve port of the three-way valve assembly through a supercritical working medium conveying pipe, and the other two valve ports of the three-way valve assembly are respectively connected to one ends of the steam generator and the ramjet mechanism through supercritical working medium conveying pipes;
the other side of the steam turbine is connected with one end of a compressor III through a supercritical working medium conveying pipe, and the other end of the compressor III is connected with a steam generator through a supercritical working medium conveying pipe connected with a three-way valve assembly;
one end of the valve port of the three-way valve assembly connected with the fuel conveying pipe is connected with one end interface of the ramjet mechanism through the fuel conveying pipe, and the other end interface is connected with the oxidant tank through the oxidant conveying pipe connected with the three-way valve assembly.
Compared with the prior art, the invention has the advantages that: the steam generators are arranged outside the combustion chambers of the rocket power mechanism and the ramjet mechanism, collect the radiant heat of the rocket engine and the ramjet combustion chamber, drive the steam turbine to do work, drive the fuel pump, the oxidant pump and the compressor to work, improve the specific impulse resistance of the rocket engine, increase the effective load, collect and convert various energies, supply energy to the rocket together, and improve the energy conversion efficiency.
And as an improvement, a three-way valve assembly of the compressor III and the steam generator is connected, and the rest valve port of the three-way valve assembly is connected to the ramjet engine mechanism through a supercritical working medium conveying pipe.
As an improvement, one end in the steam generator is provided with a rocket engine air inlet, and one side of the rocket engine air inlet is connected with a rocket engine tail nozzle through a rocket engine combustion chamber.
As an improvement, one end of the ramjet mechanism is provided with a ramjet air inlet, and one side of the ramjet air inlet is connected with a ramjet tail nozzle through a ramjet combustion chamber.
As an improvement, the outer wall of the combustion chamber of the ramjet engine is provided with a ramjet steam combined power heat conversion wall.
As an improvement, one end of the supercritical working medium conveying pipe is connected with a cooler.
Drawings
FIG. 1 is a schematic block diagram of a hybrid combined power system.
Fig. 2 is a schematic structural diagram of the embodiment.
Fig. 3 is a schematic diagram of the positions of the aircraft and the submachine of the air vehicle in the embodiment.
FIG. 4 is a schematic connection diagram of a dome steam turbine power generation system of the embodiment.
As shown in the figure: 1. a motor, 2, a clutch I, 3, a compressor I, 4, a steam turbine, 5, a fuel injector I, 6, a steam generator, 7, a three-way valve assembly, 8, a rocket engine air inlet passage, 9, a rocket engine combustion chamber, 10, a rocket engine tail nozzle, 11, a ramjet engine air inlet passage, 12, a ramjet engine combustion chamber, 13, a ramjet engine tail nozzle, 14, a fuel tank, 15, an oxidant tank, 16, a cooler, 17, a rotating shaft, 18, a supercritical working medium conveying pipe, 19, a gas turbine compressor, 20, a gas turbine combustion chamber, 21, a gas turbine high-pressure turbine, 22, a gas-steam combined power heat conversion wall, 23, a ramjet steam combined power heat conversion wall, 24, a rocket steam combined power heat conversion wall, 25, a carrier, 26, a submachine, 27, a fairing steam turbine power generation system, 28 and a rocket steam combined power system, 29. the system comprises a ram steam combined power system 30, a battery 31, a power transmission line 32, a compressor II, a compressor 33, a clutch II 34, a compressor III, a compressor 35, a fuel injector II, a fuel injector 36 and a fairing-shaped steam generator.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings.
When the hybrid combined power system is implemented specifically, the hybrid combined power system comprises a motor 1, wherein one end of the motor 1 is connected with a battery 30 through a power line 31, the other end of the motor 1 is connected with a compressor I3 through a clutch I2, the other end of the compressor I3 is coaxially provided with a compressor II 32, one end of the compressor II 32 is connected with one end of a steam turbine 4 through a clutch II 33, and the other end of the steam turbine 4 is provided with a compressor III 34;
one side of the compressor 3 is connected with a fuel tank 14 through a fuel delivery pipe, and the other side of the compressor is fixed on a fuel injector 5 of the steam generator 6 through the fuel delivery pipe connected with a three-way valve assembly 7;
one side of the second compressor 32 is connected with an oxidant tank 15 through an oxidant conveying pipe, and the other side of the second compressor is fixed on a second fuel injector 35 of the steam generator 6 through an oxidant conveying pipe connected with the three-way valve assembly 7;
one side of the steam turbine 4 is connected with one valve port of the three-way valve assembly 7 through a supercritical working medium conveying pipe 18, and the other two valve ports of the three-way valve assembly 7 are respectively connected with one end of the steam generator 6 and one end of the ramjet mechanism through the supercritical working medium conveying pipe 18;
the other side of the steam turbine 4 is connected with one end of a third compressor 34 through the supercritical working medium conveying pipe 18, and the other end of the third compressor 34 is connected with the steam generator 6 through the supercritical working medium conveying pipe 18 connected with 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 port at one end of the ramjet mechanism through the fuel delivery pipe, and the other end of the port is connected to the oxidant tank 15 through the oxidant delivery pipe connected to the three-way valve assembly 7.
The three-way valve assembly 7 connecting the compressor three 34 and the steam generator 6 has the remaining valve port connected to the ramjet mechanism through the supercritical fluid delivery pipe 18.
One end in the steam generator 6 is provided with a rocket engine air inlet passage 8, and one side of the rocket engine air inlet passage 8 is connected with a rocket engine tail nozzle 10 through a rocket engine combustion chamber 9.
Ramjet mechanism one end be equipped with ramjet intake duct 11, ramjet intake duct 11 one side be connected with ramjet exhaust port 13 through ramjet combustion chamber 12.
And a ram steam combined power heat conversion wall 23 is arranged on the outer wall of the ram engine combustion chamber 12.
One end of the supercritical working medium conveying pipe 18 is connected with a cooler 16.
The working principle of the invention is as follows: the rocket engine uses the steam generator only to collect the radiant heat of the combustion chamber to drive the steam turbine, and in order to absorb more heat, a heat exchange tube or a hollow heat exchange fin can be arranged in the combustion chamber to increase the heat exchange area.
Example (b):
one side of the motor 1 is connected with a battery 30 through a power transmission line 31, the other side of the motor is connected with the steam generator 6 through a rotating shaft 17, a first clutch 2, a first compressor 3, a second compressor 32 and a second clutch 33 are sequentially installed on the rotating shaft 17, and a third compressor 34 is coaxially installed on the other side of the second clutch 33;
one end of the compressor I3 is connected with the fuel tank 14 through a fuel delivery pipe, the other end of the compressor I is connected to one valve port of the three-way valve assembly 7, and the remaining two valve ports of the three-way valve assembly 7 are respectively connected to a fuel injector I5 of the steam generator 6 and one end interface of the ramjet mechanism through the fuel delivery pipe;
one end of the second compressor 32 is connected with the oxidant tank 15 through an oxidant conveying pipe, the other end of the second compressor is connected to one valve port of the three-way valve assembly 7, and the two remaining valve ports of the three-way valve assembly 7 are respectively connected to a second fuel injector 35 of the steam generator 6 and the other end of the ramjet mechanism through oxidant conveying pipes;
one side of the steam turbine is connected with a three-way valve assembly 7 through a supercritical working medium conveying pipe 18, and the two remaining valve ports of the three-way valve assembly 7 are respectively connected with a steam generator 6 and a ramjet mechanism through the supercritical working medium conveying pipe 18; the other side is connected with a third compressor 34 through a supercritical working medium conveying pipe 18, the other end of the third compressor 34 is connected with one valve port of a three-way valve assembly 7, and the remaining two valve ports of the three-way valve assembly 7 are respectively connected with a steam generator 6 and a ramjet mechanism through the supercritical working medium conveying pipe 18.
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 a 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 with a rocket engine combustion chamber 9 through a rocket engine air inlet duct 8, a rocket engine tail nozzle 10 is arranged on one side of the rocket engine combustion chamber 9, and a gas-steam combined power heat conversion wall 22 is installed on the outer wall of the rocket engine air inlet duct 8.
One end of the ramjet mechanism is provided with a ramjet air inlet 11, one side of the ramjet air inlet 11 is connected with a ramjet tail nozzle 13 through a ramjet combustion chamber 12, and a ramjet steam combined power heat conversion wall 23 is installed on the outer wall of the ramjet combustion chamber 12.
One end of the supercritical working medium conveying pipe 18 is connected with a cooler 16.
Compared with the original design, the embodiment 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 at the front ends of the carrier 25 and the sub-machine 26, the fairing-shaped steam turbine power generation system 27 comprises a fairing-shaped steam generator 36, two ends of the fairing-shaped steam generator 36 are connected with the steam turbine 4 through a supercritical working medium conveying pipe 18, one side of the steam turbine 4 is fixedly provided with the motor 1 through a rotating shaft, the motor 1 is connected with the battery 30 through a power transmission line 31, and the supercritical working medium conveying pipe 18 is provided with the cooler 16.
In the embodiment, the steam generator collects radiant heat of the combustion chambers of the gas turbine and the rocket engine, drives the steam turbine, and the steam turbine and the gas turbine jointly do work to drive the fuel pump, the oxidant pump and the compressor to work.
The fairing-shaped steam generator power generation system comprises a fairing-shaped steam generator, a supercritical working medium conveying pipe, a steam turbine, a motor, a rotating shaft, a power transmission line and a battery, and is used for collecting friction heat at the front end of an aircraft and generating power, and the generated power can do work through the motor.
The combined power of the rocket engine and the steam turbine is combined with the combined power of the steam turbine of the ramjet to form a power system of the aircraft, the submachine adopts the combined power of the steam turbine of the rocket engine, the aircraft firstly starts the combined power of the steam turbine of the rocket engine, when the aircraft reaches the starting speed of the ramjet, the combined power of the steam turbine of the ramjet is started, the combined power of the rocket engine is closed, when the ramjet flies at high speed, the engine is easy to overheat due to the increase of static pressure of an air inlet channel and the friction heat, before the ramjet reaches the heat-resisting limit, the submachine releases the submachine, and the submachine starts the combined power of the rocket engine to continuously fly.
The steam cycle of the present invention employs a supercritical brayton cycle.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature, and in the description of the invention, "plurality" means two or more unless explicitly defined otherwise.
In the present invention, unless otherwise specifically stated or limited, the terms "mounted," "connected," "fixed," and the like are to be construed broadly and may, for example, be fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
In the present invention, unless otherwise expressly stated or limited, "above" or "below" a first feature means that the first and second features are in direct contact, or that the first and second features are not in direct contact but are in contact with each other via another feature therebetween. Also, the first feature being "on," "above" and "over" the second feature includes the first feature being directly on and obliquely above the second feature, or merely indicating that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature includes the first feature being directly above and obliquely above the second feature, or simply meaning that the first feature is at a lesser level than the second feature.
In the description herein, reference to the terms "one embodiment," "some embodiments," "an example," "a specific example," or "some examples" or the like means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, the schematic representations of the terms used above do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.
Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made in the above embodiments by those of ordinary skill in the art without departing from the principle and spirit of the present invention.

Claims (6)

1. A hybrid combined power system comprising an electric motor (1), characterized in that: one end of the motor (1) is connected with a battery (30) through a power transmission line (31), the other end of the motor is connected with a first compressor (3) through a first clutch (2), a second compressor (32) is coaxially installed at the other end of the first compressor (3), one end of the second compressor (32) is connected with one end of a steam turbine (4) through a second clutch (33), and a third compressor (34) is arranged at the other end of the steam turbine (4);
one side of the compressor I (3) is connected with a fuel tank (14) through a fuel delivery pipe, and the other side of the compressor I is fixed on a fuel injector I (5) of the steam generator (6) through the fuel delivery pipe connected with a three-way valve assembly (7);
one side of the second compressor (32) is connected with an oxidant tank (15) through an oxidant conveying pipe, and the other side of the second compressor is fixed on a second fuel injector (35) of the steam generator (6) through the oxidant conveying pipe connected with the three-way valve assembly (7);
one side of the steam turbine (4) is connected with one valve port of the three-way valve assembly (7) through a supercritical working medium conveying pipe (18), and the other two valve ports of the three-way valve assembly (7) are respectively connected with one end of the steam generator (6) and one end of the ramjet mechanism through the supercritical working medium conveying pipe (18);
the other side of the steam turbine (4) is connected with one end of a third compressor (34) through the supercritical working medium conveying pipe (18), and the other end of the third compressor (34) is connected with the steam generator (6) through the supercritical working medium conveying pipe (18) connected with the three-way valve assembly (7);
one end of a valve port of the three-way valve assembly (7) connected with the fuel conveying pipe is connected with an interface at one end of the ramjet mechanism through the fuel conveying pipe, and the other end of the interface is connected with the oxidant tank (15) through an oxidant conveying pipe connected with the three-way valve assembly (7).
2. A hybrid combined power system as set forth in claim 1, wherein: and the three-way valve assembly (7) connecting the compressor III (34) and the steam generator (6) is connected with the rest valve port of the three-way valve assembly through the supercritical working medium conveying pipe (18) on the ramjet mechanism.
3. A hybrid combined power system as set forth in claim 1, wherein: one end in the steam generator (6) is provided with a rocket engine air inlet (8), and one side of the rocket engine air inlet (8) is connected with a rocket engine tail nozzle (10) through a rocket engine combustion chamber (9).
4. A hybrid combined power system as set forth in claim 1, wherein: ramjet mechanism one end be equipped with ramjet intake duct (11), ramjet intake duct (11) one side be connected with ramjet exhaust nozzle (13) through ramjet combustion chamber (12).
5. A hybrid combined power system as set forth in claim 4 wherein: and a stamping steam combined power heat conversion wall (23) is arranged on the outer wall of the stamping engine combustion chamber (12).
6. A hybrid combined power system as set forth in claim 4 wherein: one end of the supercritical working medium conveying pipe (18) is connected with a cooler (16).
CN201911324281.5A 2019-12-20 2019-12-20 Hybrid combined power system Withdrawn CN111075605A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201911324281.5A CN111075605A (en) 2019-12-20 2019-12-20 Hybrid combined power system

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201911324281.5A CN111075605A (en) 2019-12-20 2019-12-20 Hybrid combined power system

Publications (1)

Publication Number Publication Date
CN111075605A true CN111075605A (en) 2020-04-28

Family

ID=70316164

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201911324281.5A Withdrawn CN111075605A (en) 2019-12-20 2019-12-20 Hybrid combined power system

Country Status (1)

Country Link
CN (1) CN111075605A (en)

Similar Documents

Publication Publication Date Title
EP3623603B1 (en) Hybrid expander cycle with turbo-generator and cooled power electronics
US7836680B2 (en) Aircraft combination engines thermal management system
CN106742075B (en) Distributed propulsion system
CN108757182B (en) air-breathing rocket engine and hypersonic aircraft
WO1999066187A9 (en) Ramjet engine for power generation
CN110469871B (en) Stirling cycle-based compound cooling rotary detonation combustion chamber
CN111075564B (en) Turbine rotor engine
EP1992811B1 (en) Aircraft combination engines exhaust thrust recovery
LU501304B1 (en) A Hybrid Combined Power System
CN111075605A (en) Hybrid combined power system
CN112344372A (en) Design method of carbon dioxide-hydrocarbon fuel circulating cooling system
CN108757218B (en) Novel thermoelectric cycle combined engine
JP3236807U (en) Hybrid combined power system
CN209228489U (en) A kind of clean energy resource water circulation zero-discharging rocket engine burner electricity generation system
CN109268169A (en) A kind of clean energy resource water circulation zero-discharging rocket engine burner electricity generation system
RU2379532C1 (en) Nuclear gas turbine aircraft engine
US20130186095A1 (en) Gas turbine with motive fluid driven jet-compressor
RU2363604C1 (en) Gas turbine locomotive and its power plant
RU2375219C1 (en) Nuclear gas turbine locomotive and its power plant
CN110905690B (en) Turbine ramjet engine
CN215860492U (en) Oil-electricity hybrid power system capable of outputting power and electricity simultaneously
CN216233085U (en) High-performance cold air attitude control engine system based on turbine exhaust pipe heat exchanger
EP3566952A1 (en) Distributed propulsion system
Rodgers et al. Advances in small turbopropulsion engine technology
RU2467188C2 (en) Jet-type power plant

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination
WW01 Invention patent application withdrawn after publication

Application publication date: 20200428

WW01 Invention patent application withdrawn after publication