CN102146858A - Stamping engine for pneumatic turbine - Google Patents
Stamping engine for pneumatic turbine Download PDFInfo
- Publication number
- CN102146858A CN102146858A CN2011100374754A CN201110037475A CN102146858A CN 102146858 A CN102146858 A CN 102146858A CN 2011100374754 A CN2011100374754 A CN 2011100374754A CN 201110037475 A CN201110037475 A CN 201110037475A CN 102146858 A CN102146858 A CN 102146858A
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- China
- Prior art keywords
- turbine
- pneumatic
- pneumatic turbine
- pressed engine
- duct
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- 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.)
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Classifications
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- 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
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03D—WIND MOTORS
- F03D1/00—Wind motors with rotation axis substantially parallel to the air flow entering the rotor
- F03D1/04—Wind motors with rotation axis substantially parallel to the air flow entering the rotor having stationary wind-guiding means, e.g. with shrouds or channels
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2220/00—Application
- F05B2220/10—Application in ram-jet engines or ram-jet driven vehicles
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/10—Application in ram-jet engines or ram-jet driven vehicles
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/70—Wind energy
- Y02E10/72—Wind turbines with rotation axis in wind direction
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
- Y02P70/00—Climate change mitigation technologies in the production process for final industrial or consumer products
- Y02P70/50—Manufacturing or production processes characterised by the final manufactured product
Abstract
The invention discloses a stamping engine for a pneumatic turbine, which comprises a stamping air intake duct, a combustion chamber, a propelling spray pipe and a pneumatic turbine, wherein the stamping air intake duct is communicated with the combustion chamber; the combustion chamber is communicated with the propelling spray pipe; an air compressor is arranged in front of and/or inside the stamping air intake duct; and the pneumatic turbine is used for outputting the power for the air compressor. The stamping engine for the pneumatic turbine has no moving part in the combustion chamber and in the high-temperature air flow behind the combustion chamber, so that the manufacturing cost of a jet engine is reduced.
Description
Technical field
The present invention relates to heat energy and power field, especially a kind of pneumatic turbine pressed engine.
Background technique
The tradition pressed engine need be done high-speed motion and could obtain sufficiently high gas pressure, and then could obtain satisfied burning situation, must make the difficult problem that high-speed motion (will reach more than several Mach in general) could effectively be worked so pressed engine exists.Yet the athletic meeting of doing so at a high speed produces a series of insoluble problems, so at present remain turbojet engine and turbofan engine as what jet engine was widely used, these two kinds of motors are because rotatingshaft and combustion gas turbine all are among the high-temperature fuel gas, so be difficult to make, cost is also high, and the rotating speed of combustion gas turbine also is difficult to the level that reaches higher, because combustion gas turbine is difficult to the level that reaches higher, uses so this two classes motor also is difficult under the more speed.
If can invent a kind of advantage separately that makes full use of pressed engine and turbojet engine and contain turbofan engine, can hide the new work engine that this structure of power turbine is set again in the firing chamber, the manufacture cost of air breathing engine is reduced significantly.
Summary of the invention
In order to address the above problem, the technological scheme that the present invention proposes is as follows:
A kind of pneumatic turbine pressed engine, comprise ram air duct, firing chamber, propelling nozzle and pneumatic turbine, described ram air duct is communicated with described firing chamber, described firing chamber is communicated with described propelling nozzle, gas compressor is established in the place ahead and/or inside in described ram air duct, and described pneumatic turbine is to described gas compressor outputting power.
Described gas compressor is located at the front portion of described ram air duct.
Described gas compressor is located at the middle part of described ram air duct.
Described gas compressor is located at the rear portion of described ram air duct.
Described gas compressor is located at the high static pressure district that is positioned at the described ram air duct before the described firing chamber.
Described pneumatic turbine through speed changer to described gas compressor outputting power.
Described speed changer is made as the magnetic gear-shift transmission.
Described pneumatic turbine is set up in parallel on the direction vertical with direction of advance with described gas compressor.
Described pneumatic turbine pressed engine also comprises oxidizer source, establishes high-pressure oxidation agent introducing port on described firing chamber, and described oxidizer source is communicated with described high-pressure oxidation agent introducing port through the oxygenant high-pressure service pump.
Described pneumatic turbine pressed engine also comprises rocket motor, and described rocket motor and described propelling nozzle are set up in parallel.
Described pneumatic turbine pressed engine also comprises pneumatic turbine duct, and described pneumatic turbine is located in the described pneumatic turbine duct, and described ram air duct is located in the described pneumatic turbine duct.
Described pneumatic turbine pressed engine also comprises pneumatic turbine duct, and described pneumatic turbine is located in the described pneumatic turbine duct, and described pneumatic turbine duct is located in the described ram air duct.
Described pneumatic turbine pressed engine also comprises pneumatic turbine duct, and described pneumatic turbine is located in the described pneumatic turbine duct, and described ram air duct and described pneumatic turbine duct are set up in parallel.
Principle of the present invention is that the air-flow of the relative high-speed motion that forms beyond the ramjet engine air inlet when utilizing pressed engine to make straight line, curve or circular movement promotes pneumatic turbine, this pneumatic turbine is to being arranged on the gas compressor outputting power of scramjet combustor upstream, the air-flow that this gas compressor will enter ramjet engine air inlet and/or will enter ramjet engine air inlet carries out the speedup supercharging, this is converted to kinetic energy the pressure energy by the air-flow of speedup supercharging in the anallobar of ramjet engine air inlet, pressure further improves, and forms the efficient burning condition.Air inlet and fuel spray at a high speed by propelling nozzle after the internal combustion of firing chamber, make pressed engine obtain Driving force.
Pressed engine is the simplest motor of present structure, but because its structure and circulation form make high velocity air to compress self, so just requiring high velocity air to have quite high speed (being kinetic energy) just can make the pressure in the firing chamber reach due height, form good combustion efficient and high velocity jet air-flow, realize high Driving force for pressed engine and create conditions.In order to realize this process, the movement velocity of pressed engine is reached more than several Mach, seriously like this limited the pressed engine practical application.The essence of pneumatic turbine pressed engine disclosed in this invention utilizes a part of high velocity air to help another part high velocity air to reach needed punching press condition and static pressure pressure exactly, realize the efficient operation of pressed engine, its essence is stamping pressure and superimposed, to improve the pressure of the preceding air-flow of pressed engine internal combustion reaction by the gas pressure that gas compressor produced that pneumatic turbine drove.
Pneumatic turbine pressed engine disclosed in this invention is owing to do not need the resistant to elevated temperatures power turbine that involves great expense in the firing chamber and in the later high temperature gas flow in firing chamber, so can produce the low air breathing engine of cost, can be used to make all kinds of aircraft, as aircraft, guided missile etc.
Among the present invention, so-called pneumatic turbine is meant the turbine (being impeller mechanism) of outputting power under the air-flow effect; So-called ram air duct is meant the intake duct (being also referred to as Diffuser) of pressed engine, and high velocity air portion within it changes into the pressure energy with kinetic energy; So-called propelling nozzle is meant the jet pipe that the energy of high temperature and high pressure gas is become the kinetic energy high velocity jet acquisition reaction force of gas; So-called gas compressor is meant the impeller type gas compressor, and air is boosted in gas compressor; So-called pneumatic turbine duct is meant that inside is provided with the gas channel of pneumatic turbine, and its effect is to utilize high velocity air more effectively to shift pneumatic turbine onto.
So-called " described pneumatic turbine is to described gas compressor outputting power " is meant that described pneumatic turbine rotates among the present invention under the effect of air-flow, utilize this rotating power that described gas compressor is rotated, another strand air-flow is carried out supercharging, described pneumatic turbine can be any one transmission form to the form of described gas compressor transmission power, for example coaxial transmission, through the gear transmission etc.; Described pneumatic turbine is by adjusting velocity ratio to satisfy the requirement of different operating modes such as aircraft takeoff, continuation of the journey and landing through gear to the purpose that described gas compressor transmits power.
Among the present invention, the purpose that oxidizer source is set is in order to satisfy the requirement of different operating modes such as aircraft takeoff, continuation of the journey and landing to motor power, for example when aircraft takeoff, because speed is lower, the boosting capability of described gas compressor also can be lower, and at this moment can to increase thrust, only need in described firing chamber, import oxygenant where necessary by in described firing chamber, importing oxygenant and increasing the amount of fuel.The purpose that rocket motor is set in the system of the disclosed pneumatic turbine pressed engine of the present invention also is in order to satisfy the requirement of different operating modes such as aircraft takeoff, continuation of the journey and landing to motor power, and described rocket motor can only be worked where necessary.
Among the present invention, so-called the place ahead is meant from the reciprocal sensing of ram air duct import to air current flow; So-called upstream is meant the upstream of air current flow; So-called oxygenant be meant can with the material of fuel generation combustion chemistry reaction, as oxygen, hydrogen peroxide etc.
Among the present invention, so-called high static pressure district is meant the preceding higher zone of gas pressure of the burning that is in the described ram air duct; The purpose that described gas compressor is located in the high static pressure district is in order to improve the working efficiency of described gas compressor.
In the disclosed pneumatic turbine pressed engine of the present invention, described pneumatic turbine can be made as the adjustable pneumatic turbine in angle down with the wind, to satisfy the needs of different operating modes.
Among the present invention, the known technology according to heat energy and power field (comprising the air breathing engine field) is provided with all necessary parts, unit and systems such as valve, pump, sensor, all kinds of mechanism, control system in the place of necessity.
In the disclosed pneumatic turbine pressed engine of the present invention, can in described ram air duct, establish high-pressure oxidation agent jetburner when being necessary and/or in described propelling nozzle, establish the high-pressure working medium jetburner with helping pneumatic turbine pressed engine startup disclosed in this invention.
Beneficial effect of the present invention is as follows:
In the disclosed pneumatic turbine pressed engine of the present invention, in the later high temperature gas flow in firing chamber and firing chamber, there is not moving element, reduced the manufacture cost of jet engine.
Description of drawings
Fig. 1 is the structural representation of the embodiment of the invention 1;
Fig. 2 is the structural representation of the embodiment of the invention 2;
Fig. 3 is the structural representation of the embodiment of the invention 3;
Fig. 4 is the structural representation of the embodiment of the invention 4;
Fig. 5 is that the A-A of Fig. 4 is to sectional view;
Fig. 6 is the structural representation of the embodiment of the invention 5;
Fig. 7 is the structural representation of the embodiment of the invention 6;
Fig. 8 is the structural representation of the embodiment of the invention 7;
Fig. 9 is the structural representation of the embodiment of the invention 8;
Figure 10 is the structural representation of the embodiment of the invention 9;
Figure 11 is the structural representation of the embodiment of the invention 10.
Embodiment
Pneumatic turbine pressed engine as shown in Figure 1, comprise ram air duct 1, firing chamber 2, propelling nozzle 3 and pneumatic turbine 4, ram air duct 1 is communicated with firing chamber 2, firing chamber 2 is communicated with propelling nozzle 3, gas compressor 100 is established in inside, the place ahead in ram air duct 1,4 pairs of gas compressor 100 outputting powers of pneumatic turbine.
During concrete enforcement, described gas compressor 100 can also be located at the front portion of described ram air duct 1, or described gas compressor 100 is located at the middle part of described ram air duct 1, or described gas compressor 100 is located at the rear portion of described ram air duct 1; The purpose of She Zhiing is in order to improve the efficient of described gas compressor 100 like this.
Pneumatic turbine pressed engine as shown in Figure 2, itself and embodiment's 1 difference is: pneumatic turbine pressed engine also comprises pneumatic turbine duct 5, and pneumatic turbine 4 is located in the pneumatic turbine duct 5, and ram air duct 1 is located in the pneumatic turbine duct 5.
Pneumatic turbine pressed engine as shown in Figure 3, itself and embodiment's 2 difference is: establish gas compressor 100 in the inside of ram air duct 1, gas compressor 100 is located at the high static pressure district that is positioned at the ram air duct 1 before the firing chamber 2.The purpose that described gas compressor is located in the high static pressure district is in order to improve the working efficiency of described gas compressor.
Pneumatic turbine pressed engine as shown in Figure 4 and Figure 5, itself and embodiment's 1 difference is: pneumatic turbine pressed engine also comprises pneumatic turbine duct 5, and pneumatic turbine 4 is located in the pneumatic turbine duct 5, and pneumatic turbine duct 5 is located in the ram air duct 1.
Pneumatic turbine pressed engine as shown in Figure 6, itself and embodiment's 1 difference is: pneumatic turbine pressed engine also comprises pneumatic turbine duct 5, and pneumatic turbine 4 is located in the pneumatic turbine duct 5, and ram air duct 1 and pneumatic turbine duct 5 are set up in parallel.
Pneumatic turbine pressed engine as shown in Figure 7, itself and embodiment's 3 difference is: pneumatic turbine 4 is through 410 pairs of gas compressor 100 outputting powers of speed changer.Described pneumatic turbine is by adjusting velocity ratio to satisfy the requirement of different operating modes such as aircraft takeoff, continuation of the journey and landing through speed changer to the purpose of described gas compressor outputting power.
Embodiment 7
Pneumatic turbine pressed engine as shown in Figure 8, itself and embodiment's 6 difference is: speed changer 410 is made as magnetic gear-shift transmission 411.
Embodiment 8
Pneumatic turbine pressed engine as shown in Figure 9, its difference with embodiment 1 is: described pneumatic turbine 4 is set up in parallel on the direction vertical with direction of advance with described gas compressor 100.
Embodiment 9
Pneumatic turbine pressed engine as shown in figure 10, itself and embodiment's 1 difference is: described pneumatic turbine pressed engine also comprises oxidizer source 2001, establish high-pressure oxidation agent introducing port 200 on described firing chamber 2, described oxidizer source 2001 is communicated with described high-pressure oxidation agent introducing port 200 through oxygenant high-pressure service pump 2002.The purpose that oxidizer source is set is in order to satisfy the requirement of different operating modes such as aircraft takeoff, continuation of the journey and landing to motor power, for example when aircraft takeoff, because speed is lower, the boosting capability of described gas compressor also can be lower, and at this moment can be by in described firing chamber, importing oxygenant and increasing the amount of fuel, with increase thrust, but only need in described firing chamber, import oxygenant where necessary.
Embodiment 10
Pneumatic turbine pressed engine as shown in figure 11, itself and embodiment's 1 difference is: described pneumatic turbine pressed engine also comprises rocket motor 3000, described rocket motor 3000 is set up in parallel with described propelling nozzle 3.The purpose that rocket motor is set also is in order to satisfy the requirement of different operating modes such as aircraft takeoff, continuation of the journey and landing to motor power, and described rocket motor can only be worked where necessary.
Obviously, the invention is not restricted to above embodiment, many distortion can also be arranged.Those of ordinary skill in the art, all distortion that can directly derive or associate from content disclosed by the invention all should be thought protection scope of the present invention.
Claims (13)
1. pneumatic turbine pressed engine, comprise ram air duct (1), firing chamber (2), propelling nozzle (3) and pneumatic turbine (4), it is characterized in that: described ram air duct (1) is communicated with described firing chamber (2), described firing chamber (2) is communicated with described propelling nozzle (3), gas compressor (100) is established in the place ahead and/or inside in described ram air duct (1), and described pneumatic turbine (4) is to described gas compressor (100) outputting power.
2. pneumatic according to claim 1 turbine pressed engine is characterized in that: described gas compressor (100) is located at the front portion of described ram air duct (1).
3. pneumatic according to claim 1 turbine pressed engine is characterized in that: described gas compressor (100) is located at the middle part of described ram air duct (1).
4. pneumatic according to claim 1 turbine pressed engine is characterized in that: described gas compressor (100) is located at the rear portion of described ram air duct (1).
5. pneumatic according to claim 1 turbine pressed engine is characterized in that: described gas compressor (100) is located at the high static pressure district that is positioned at the preceding described ram air duct (1) in described firing chamber (2).
6. pneumatic according to claim 1 turbine pressed engine is characterized in that: described pneumatic turbine (4) through speed changer (410) to described gas compressor (100) outputting power.
7. as pneumatic turbine pressed engine as described in the claim 6, it is characterized in that: described speed changer (410) is made as magnetic gear-shift transmission (411).
8. pneumatic according to claim 1 turbine pressed engine is characterized in that: described pneumatic turbine (4) is set up in parallel on the direction vertical with direction of advance with described gas compressor (100).
9. pneumatic according to claim 1 turbine pressed engine, it is characterized in that: described pneumatic turbine pressed engine also comprises oxidizer source (2001), establish high-pressure oxidation agent introducing port (200) on described firing chamber (2), described oxidizer source (2001) is communicated with described high-pressure oxidation agent introducing port (200) through oxygenant high-pressure service pump (2002).
10. pneumatic according to claim 1 turbine pressed engine is characterized in that: described pneumatic turbine pressed engine also comprises rocket motor (3000), and described rocket motor (3000) is set up in parallel with described propelling nozzle (3).
11. as pneumatic turbine pressed engine as described in the claim 1,2,3,4,5,6,7,9 or 10, it is characterized in that: described pneumatic turbine pressed engine also comprises pneumatic turbine duct (5), described pneumatic turbine (4) is located in the described pneumatic turbine duct (5), and described ram air duct (1) is located in the described pneumatic turbine duct (5).
12. as pneumatic turbine pressed engine as described in the claim 1,2,3,4,5,6,7,9 or 10, it is characterized in that: described pneumatic turbine pressed engine also comprises pneumatic turbine duct (5), described pneumatic turbine (4) is located in the described pneumatic turbine duct (5), and described pneumatic turbine duct (5) is located in the described ram air duct (1).
13. as pneumatic turbine pressed engine as described in the claim 8,9 or 10, it is characterized in that: described pneumatic turbine pressed engine also comprises pneumatic turbine duct (5), described pneumatic turbine (4) is located in the described pneumatic turbine duct (5), and described ram air duct (1) and described pneumatic turbine duct (5) are set up in parallel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011100374754A CN102146858A (en) | 2010-08-12 | 2011-02-14 | Stamping engine for pneumatic turbine |
Applications Claiming Priority (5)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201010251824.8 | 2010-08-12 | ||
| CN201010251824 | 2010-08-12 | ||
| CN201010287674 | 2010-09-20 | ||
| CN201010287674.6 | 2010-09-20 | ||
| CN2011100374754A CN102146858A (en) | 2010-08-12 | 2011-02-14 | Stamping engine for pneumatic turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102146858A true CN102146858A (en) | 2011-08-10 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011100374754A Pending CN102146858A (en) | 2010-08-12 | 2011-02-14 | Stamping engine for pneumatic turbine |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN102146858A (en) |
| WO (1) | WO2012019419A1 (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106703993A (en) * | 2015-11-14 | 2017-05-24 | 熵零股份有限公司 | Engine |
| CN106704031A (en) * | 2015-11-14 | 2017-05-24 | 熵零股份有限公司 | Engine |
| CN106704033A (en) * | 2015-11-14 | 2017-05-24 | 熵零股份有限公司 | Method for constructing power system and device thereof |
| CN106704032A (en) * | 2015-11-14 | 2017-05-24 | 熵零股份有限公司 | Engine |
| CN110486170A (en) * | 2017-08-29 | 2019-11-22 | 熵零技术逻辑工程院集团股份有限公司 | A kind of axis transmission injection-type engine cooling system |
| CN114790955A (en) * | 2022-05-06 | 2022-07-26 | 哈尔滨工业大学 | Hybrid power engine capable of realizing oil-electricity range extension |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114215788A (en) * | 2021-11-30 | 2022-03-22 | 中国航发沈阳发动机研究所 | Counter-rotating stamping gas compressor |
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| US5085041A (en) * | 1988-03-23 | 1992-02-04 | Rolls-Royce Plc | Dual mode engine having a continuously operated oxidizer pump |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN106703993A (en) * | 2015-11-14 | 2017-05-24 | 熵零股份有限公司 | Engine |
| CN106704031A (en) * | 2015-11-14 | 2017-05-24 | 熵零股份有限公司 | Engine |
| CN106704033A (en) * | 2015-11-14 | 2017-05-24 | 熵零股份有限公司 | Method for constructing power system and device thereof |
| CN106704034A (en) * | 2015-11-14 | 2017-05-24 | 熵零股份有限公司 | Method for constructing power system and device for method |
| CN106704032A (en) * | 2015-11-14 | 2017-05-24 | 熵零股份有限公司 | Engine |
| CN110486170A (en) * | 2017-08-29 | 2019-11-22 | 熵零技术逻辑工程院集团股份有限公司 | A kind of axis transmission injection-type engine cooling system |
| CN114790955A (en) * | 2022-05-06 | 2022-07-26 | 哈尔滨工业大学 | Hybrid power engine capable of realizing oil-electricity range extension |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2012019419A1 (en) | 2012-02-16 |
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Application publication date: 20110810 |