CN106762221A - Turbo ramjet engine ram-air turbine heat to electricity conversion and forecooling method - Google Patents
Turbo ramjet engine ram-air turbine heat to electricity conversion and forecooling method Download PDFInfo
- Publication number
- CN106762221A CN106762221A CN201710025514.6A CN201710025514A CN106762221A CN 106762221 A CN106762221 A CN 106762221A CN 201710025514 A CN201710025514 A CN 201710025514A CN 106762221 A CN106762221 A CN 106762221A
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- Prior art keywords
- turbogenerator
- ramjet
- intake duct
- air
- air intake
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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
-
- 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
- F02K7/16—Composite ram-jet/turbo-jet engines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
- F01D15/10—Adaptations for driving, or combinations with, electric generators
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D17/00—Regulating or controlling by varying flow
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
-
- 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
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/057—Control or regulation
Abstract
Turbo ramjet engine ram-air turbine heat to electricity conversion and forecooling method, are related to combined engine.Offer combined engine aircraft power demands and realizes turbogenerator inlet flow precooling purpose when can meet High Mach number flight, simple structure, and air inflow is adjustable, moreover it is possible to reduce the turbo ramjet engine ram-air turbine heat to electricity conversion and forecooling method of the spillage drag of ramjet air intake duct.When flight Mach number reaches 2, turbogenerator starts to progressively close off, and ramjet air intake duct is opened, and ramjet is started working；When turbogenerator air intake duct is completely closed, turbogenerator is completely closed.Solve the problems such as existing combined engine aviation power supply in hypersonic flight is not enough, and gas flow temperature is too high before turbogenerator compressor when turbogenerator and ramjet work simultaneously.
Description
Technical field
The present invention relates to combined engine field, more particularly, to a kind of turbo ramjet engine ram-air turbine
Heat to electricity conversion and forecooling method.
Background technology
Speed domain wide Power System of Flight Vehicle does not require nothing more than the ability for being freely accessible near space, also requires high-altitude high-performance cruise
Ability to work, at the same near space vehicle dynamical system should possess high-performance, lightweight, voyage highly reliable, inexpensive, long,
Exempt from other features such as boosting, reusable, speed-adaptive wide ranges.Existing aero-engine, rocket engine and punching
Pressure jet engine is difficult to meet above-mentioned requirements due to self-technique reason.
By combining existing ripe power set, realize aircraft fast domain autonomous flight wide, be aviation military power in recent years
It is also one of important direction of China's sky day research field come the focus studied.Combined cycle engine is by low-speed range (Ma0
~Ma3) ramjet that uses of the turbine base engine that uses and high-speed range (Ma3~Ma5) constitutes, referred to as whirlpool
Wheel-punching press combined engine (Turbine Based Combined Cycle, TBCC).TBCC can be led due to it as tactics
Bullet, cruise missile, target drone, inexpensive high-speed flight test platform, the power set of the first order propulsion system of orbiter,
It is that China turns into one of important disruptive technology of Kong Tian military powers, with important military requirement and value.
The thrust wide gap that turbine rotor mode turns punching press mode at this stage is the key technology for being badly in need of breaking through, in order to ensure
The continuity of mode conversion process thrust, it is main at present by developing high-speed turbine engine, expanding whirlpool by the pre- refrigeration technique of jet
Turbine envelope curve, strong precooling turborocket technology, Rocket ejector punching press combination and continuous pinking combination technique etc. are realized.No matter adopt
Which kind of technology is used, the heat management of combined engine and energy management are all its problem demanding prompt solutions.TBCC is in from turbine hair
The transition stage that motivation operation mode is changed to ramjet operation mode, the air-flow temperature in turbogenerator air intake duct
Degree may beyond compressor can bearing temperature scope, cause compressor to damage, so reduce turbogenerator service life.
Further, since the supply of the onboard electric energy is transformed by the part turbine work(of turbogenerator in flight course,
When aircraft is in ramjet operation mode, turbogenerator does not work, now the supply of the onboard electric energy
In order to one need solve problem.
The content of the invention
The purpose of the present invention is directed to existing combined engine aviation power supply deficiency in hypersonic flight, in turbine
The problems such as gas flow temperature is too high before turbogenerator compressor engine works with ramjet simultaneously when, there is provided can expire
Combined engine aircraft power demands and turbogenerator inlet flow precooling purpose is realized during sufficient High Mach number flight, tied
Structure is simple, and air inflow is adjustable, moreover it is possible to reduce the turboram combination hair of the spillage drag of ramjet air intake duct
Motivation ram-air turbine heat to electricity conversion and forecooling method.
The present invention is comprised the following steps：
1) when flight Mach number reaches 2, turbogenerator starts to progressively close off, and ramjet air intake duct is beaten
Open, ramjet is started working；
In step 1) in, described when flight Mach number reaches 2, turbogenerator starts to progressively close off, punching jetting hair
Motivation air intake duct is opened, and what ramjet was started working comprises the following steps that：
(1) air inlet and gas outlet are opened completely, introduce high temperature gas flow；
(2) high temperature gas flow promotes the acting of punching press turbine；
(3) air-flow after doing work returns to turbogenerator air intake duct by gas outlet.
2) when turbogenerator air intake duct is completely closed, turbogenerator is completely closed.
In step 2) in, when the turbogenerator air intake duct is completely closed, the specific step that turbogenerator is completely closed
It is rapid as follows：
(1) gas outlet is opened；
(2) high temperature gas flow promotes the acting of punching press turbine；
(3) control gas outlet goes out throughput, and the air-flow after making part do work in turbogenerator air intake duct to that may deposit
High temperature earial drainage cooled down；
(4) another part air-flow after doing work returns to ramjet air intake duct by gas outlet.
The present invention gives a kind of turbo ramjet engine ram-air turbine heat to electricity conversion and pre- refrigeration technique, solve
Existing combined engine aviation power supply in hypersonic flight is not enough, same with ramjet in turbogenerator
When work when turbogenerator compressor before gas flow temperature it is too high the problems such as.
The method have the characteristics that：
Go out throughput by adjust gas outlet in turbogenerator air intake duct, after make use of punching press turbine in part to do work
Low-temperature airflow completely closes rear high temperature earial drainage that may be present to the high temperature gas flow and air intake duct in turbogenerator air intake duct and enters
Row cooling, so as to reach the precooling purpose of turbogenerator；After turbogenerator is stopped, heat is carried out using punching press turbine
Electricity conversion, supplements onboard electric；By controlling the air inflow size of air inlet in ramjet air intake duct, can moderately adjust
The air inflow of ramjet is saved, so as to reduce spillage drag.
Brief description of the drawings
Fig. 1 is the principle of turbo ramjet engine ram-air turbine heat to electricity conversion of the present invention and forecooling method
Figure.
Fig. 2 is the implementation of turbo ramjet engine ram-air turbine heat to electricity conversion of the present invention and forecooling method
Example overall structure diagram.
In fig. 2, each mark for：1 is turbogenerator air intake duct, and 2 is turbogenerator air intake duct controlling switch, and 3 are
Air inlet in ramjet air intake duct, 4 is ramjet air intake duct, and 5 is punching press turbine inlet, and 6 are
Punching press turbine, 7 is the gas outlet in ramjet air intake duct, and 8 is ramjet, and 9 is turbogenerator, 10
It is the gas outlet in turbogenerator air intake duct.
Specific embodiment
Fig. 1 provides the schematic diagram of the turbo ramjet engine ram-air turbine heat to electricity conversion and forecooling method,
There is an air inlet in ramjet air intake duct, direct flow into punching press-turbine apparatus front end (T1), in punching
Pressure-turbine rear end returns to turbogenerator by gas outlet T2 respectively and another gas outlet returns to ramjet air intake duct
It is interior.When flight Mach number is less than 2, turbogenerator work, ramjet do not work, and now air inlet and two go out
Gas port is all closed, and punching press turbine does not work；When flight Mach number reaches 2, turbogenerator is progressively closed off, and punching jetting starts
Machine is started working, and now turbogenerator air intake duct interior air-flow temperature is too high, is easily damaged compressor, now, positioned at punching press spray
Air inlet in gas engine inlets is controlled to open by dividing plate, the High Temperature Gas in suction part ramjet air intake duct
Stream, then air-flow promotion punching press turbine acting, its interior energy and kinetic energy are converted into the mechanical energy of turbine, can be further converted to electric energy
To generator, for onboard electric energy supply, heat to electricity conversion is achieved in, and air-flow interior energy reduces, temperature reduction, Ran Houtong
The gas outlet crossed in turbogenerator air intake duct returns to and is sufficiently mixed with high temperature gas flow therein in turbogenerator air intake duct, makes
Mixed gas temperature is less than inlet air flow temperature, realizes precooling function；When turbogenerator is completely closed, turbine is now placed in
Gas outlet regulation outlet uninterrupted in engine inlets, continues cooling turbine engines, to prevent height that may be present
Warm earial drainage damages turbogenerator, and the gas outlet in ramjet air intake duct is opened, and high temperature gas flow promotes turbine
Acting, continues to realize heat to electricity conversion, then air-flow returns to punching jetting by the gas outlet in ramjet air intake duct
In engine inlets, increase air flow rate.In addition, when ramjet works, because ramjet enters
The presence of air inlet in air flue, the increase of ramjet air intake duct total sectional area, then air inflow increase, while can also reduce
The spillage drag of air intake duct.
As shown in Fig. 2 overall structure includes air inlet 3, the punching press turbine inlet in ramjet air intake duct
5th, the gas outlet 7 in punching press turbine 6, ramjet air intake duct, the gas outlet 10 in turbogenerator air intake duct.It is described
Air inlet 3 in ramjet air intake duct can be controlled the size of air inflow by mechanical device.Described punching press turbine 6 can
Electric power supplement is carried out to the airborne energy.Gas outlet 7 and turbogenerator air inlet in described ramjet air intake duct
Gas outlet 10 in road can be controlled the size of exit flow flow by mechanical device.
Turbo ramjet engine ram-air turbine heat to electricity conversion of the present invention and forecooling method include following step
Suddenly：
1) when flight Mach number reaches two, turbogenerator 9 starts to progressively close off, ramjet air intake duct 4
Open, ramjet 8 is started working：
(1) air inlet 3, gas outlet 10 are opened completely, introduce high temperature gas flow；
(2) high temperature gas flow promotes punching press turbine 6 to do work；
(3) air-flow after doing work returns to turbogenerator air intake duct 1 by gas outlet 10.
2) when turbogenerator air intake duct 2 is completely closed, turbogenerator is completely closed：
(1) gas outlet 7 is opened；
(2) high temperature gas flow promotes punching press turbine 6 to do work；
(3) control gas outlet 10 goes out throughput, and the air-flow after making part do work is to possible in turbogenerator air intake duct
The high temperature earial drainage of presence is cooled down；
(4) another part air-flow after doing work returns to ramjet air intake duct 4 by gas outlet 7.
Specific work process given below：
Turbo ramjet engine ram-air turbine heat to electricity conversion and forecooling method are main by turbogenerator air inlet
The air inlet 3 before gas outlet 10, ramjet air intake duct in road, the gas outlet in ramjet air intake duct
7 and punching press turbine 6 constitute.When aircraft flight Mach number is less than 2, turbogenerator air intake duct 2 is opened, turbogenerator work
Make, ramjet air intake duct 4 is closed, and ramjet is not worked, and now air inlet 3, gas outlet 10 and 7 are all closed
Close, punching press turbine 6 does not work；When flight Mach number reaches 2, turbogenerator is progressively closed off, ramjet air inlet
Road 4 is opened, and ramjet is started working, and air inlet 3, gas outlet 10 are opened, and high temperature gas flow is introduced, now, due to entering
The presence of gas port 3, the increase of ramjet air intake duct total sectional area, then air inflow increase, can reduce the overflow of air intake duct
Resistance, then high temperature gas flow promote punching press turbine 6 to do work, its interior energy and kinetic energy are converted into the mechanical energy of turbine, can further turn
Electric energy is turned to for onboard electric energy supply, heat to electricity conversion is achieved in, while its interior energy reduces, temperature reduction, by going out
Gas port 10 is returned to and is sufficiently mixed with high temperature gas flow therein in turbogenerator air intake duct, mixed gas temperature is less than into implication
Stream temperature, realizes precooling function；When turbogenerator is completely closed, turbogenerator air intake duct 2 is closed, now gas outlet 10
Regulation outlet uninterrupted, continues cooling turbine engines, to prevent high temperature earial drainage that may be present from damaging turbogenerator, punching
Gas outlet 7 is opened in pressure jet engine inlet, and high temperature gas flow promotes punching press turbine 6 to do work, and continues to realize heat to electricity conversion, so
Air-flow is returned in ramjet air intake duct by the gas outlet 7 in ramjet air intake duct afterwards, increases air-flow
Flow.
Claims (3)
1. turbo ramjet engine ram-air turbine heat to electricity conversion and forecooling method, it is characterised in that including following step
Suddenly：
1) when flight Mach number reaches 2, turbogenerator starts to progressively close off, and ramjet air intake duct is opened, punching
Pressure jet engine is started working；
2) when turbogenerator air intake duct is completely closed, turbogenerator is completely closed.
2. turbo ramjet engine ram-air turbine heat to electricity conversion as claimed in claim 1 and forecooling method, its feature
It is in step 1) in, described when flight Mach number reaches 2, turbogenerator starts to progressively close off, ramjet
Air intake duct is opened, and what ramjet was started working comprises the following steps that：
(1) air inlet and gas outlet are opened completely, introduce high temperature gas flow；
(2) high temperature gas flow promotes the acting of punching press turbine；
(3) air-flow after doing work returns to turbogenerator air intake duct by gas outlet.
3. turbo ramjet engine ram-air turbine heat to electricity conversion as claimed in claim 1 and forecooling method, its feature
It is in step 2) in, when the turbogenerator air intake duct is completely closed, the specific steps that turbogenerator is completely closed are such as
Under：
(1) gas outlet is opened；
(2) high temperature gas flow promotes the acting of punching press turbine；
(3) control gas outlet goes out throughput, and the air-flow after making part do work is to that may be present in turbogenerator air intake duct
High temperature earial drainage is cooled down；
(4) another part air-flow after doing work returns to ramjet air intake duct by gas outlet.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710025514.6A CN106762221B (en) | 2017-01-13 | 2017-01-13 | Turbo ramjet engine ram-air turbine heat to electricity conversion and forecooling method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710025514.6A CN106762221B (en) | 2017-01-13 | 2017-01-13 | Turbo ramjet engine ram-air turbine heat to electricity conversion and forecooling method |
Publications (2)
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| CN106762221A true CN106762221A (en) | 2017-05-31 |
| CN106762221B CN106762221B (en) | 2018-10-26 |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108317012A (en) * | 2018-01-22 | 2018-07-24 | 哈尔滨工程大学 | A kind of fluidic device suitable for high Mach number engine air inlet precooling |
| CN108757218A (en) * | 2018-05-30 | 2018-11-06 | 北京理工大学 | A kind of novel thermoelectric cycle combined engine |
| CN108843460A (en) * | 2018-06-28 | 2018-11-20 | 厦门大学 | Heat to electricity conversion and pushing method is pre-chilled in turbo ramjet engine |
| CN113279880A (en) * | 2021-07-06 | 2021-08-20 | 中国航空发动机研究院 | Combined cycle aircraft engine |
| CN114704384A (en) * | 2022-04-24 | 2022-07-05 | 中国航发沈阳发动机研究所 | Method and structure for cooling turbine engine cabin of hypersonic vehicle |
| CN117401171A (en) * | 2023-12-13 | 2024-01-16 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Method and device for switching modes in transition stage of power system of high-speed aircraft |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN108317012A (en) * | 2018-01-22 | 2018-07-24 | 哈尔滨工程大学 | A kind of fluidic device suitable for high Mach number engine air inlet precooling |
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| CN113279880B (en) * | 2021-07-06 | 2022-11-11 | 中国航空发动机研究院 | Combined cycle aircraft engine |
| CN114704384A (en) * | 2022-04-24 | 2022-07-05 | 中国航发沈阳发动机研究所 | Method and structure for cooling turbine engine cabin of hypersonic vehicle |
| CN117401171A (en) * | 2023-12-13 | 2024-01-16 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Method and device for switching modes in transition stage of power system of high-speed aircraft |
| CN117401171B (en) * | 2023-12-13 | 2024-03-08 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Method and device for switching modes in transition stage of power system of high-speed aircraft |
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| CN106762221B (en) | 2018-10-26 |
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Inventor after: Huang Yue Inventor after: Lin Xi Inventor after: Luan Zhenye Inventor after: Mao Zhiwei Inventor after: Lin Keli Inventor after: Peng Han Inventor after: Zhu Jianfeng Inventor after: Li Aicheng Inventor before: Huang Yue Inventor before: Lin Xi Inventor before: Luan Zhenye Inventor before: Mao Zhiwei Inventor before: Lin Keli Inventor before: Peng Han Inventor before: Zhu Jianfeng |
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