CN113864050A - Detonation supercharging aircraft engine - Google Patents
Detonation supercharging aircraft engine Download PDFInfo
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- CN113864050A CN113864050A CN202111108196.2A CN202111108196A CN113864050A CN 113864050 A CN113864050 A CN 113864050A CN 202111108196 A CN202111108196 A CN 202111108196A CN 113864050 A CN113864050 A CN 113864050A
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- Prior art keywords
- rotary valve
- detonation
- combustion chamber
- gas
- detonation tube
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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
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/16—Control of working fluid flow
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R7/00—Intermittent or explosive combustion chambers
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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
- F05D2270/00—Control
- F05D2270/01—Purpose of the control system
- F05D2270/05—Purpose of the control system to affect the output of the engine
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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
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/12—Improving ICE efficiencies
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Supercharger (AREA)
Abstract
The utility model provides a knockings supercharged turbo engine, including the compressor, the rotary valve admits air, the detonation tube combustion chamber, the rotary valve of giving vent to anger, the turbine, the machine casket, the rotor shaft, speed adjusting device, the detonation tube combustion chamber front end and rear end have respectively admit air the rotary valve and give vent to anger the rotary valve movive seal, admit air the rotary valve and give vent to anger the rotary valve and pass through the speed adjusting device and fix on the rotor shaft, rotate along with the rotor, the detonation tube is fixed in on the machine casket, the axial is equipped with a plurality of passageways, radial circumference array distributes, after gaseous entering detonation tube mixes with fuel nozzle blowout fuel, ignite the burning by some firearm. The gas inlet and the gas outlet are distributed in a staggered manner, so that the gas can knock in the detonation tube to perform constant volume combustion. The inlet rotary valve is located downstream of the compressor and the outlet rotary valve is located upstream of the turbine. The invention uses the combustion chamber with large slenderness ratio to match with the inlet and outlet rotary valves to realize the constant volume detonation combustion, improves the cycle efficiency of the engine compared with an isobaric combustion engine, simplifies the design of a gas compressor and a turbine and improves the performance of the engine.
Description
Technical Field
The invention relates to the technical field of aviation turbine engines and gas turbines, in particular to a single-rotor detonation supercharged turbine engine.
Background
In a conventional axial flow type aircraft engine, the improvement of the pressure ratio of a gas compressor and the temperature of gas before a turbine is an important way for improving the ideal cycle power and the thermal efficiency of the engine, and the pressure ratio of the gas compressor is mainly realized by improving the rotating speed of a rotor blade of the gas compressor and an advanced blade shape design. Subject to the material technology, the greater the rotational speed, the greater the centrifugal force to which the rotor blade is subjected, so that it is not possible to increase the rotational speed indefinitely; and the blade tip is easy to form a supersonic speed area to generate shock waves, so that shock wave loss is caused. There are also theoretical limits to advanced lobe designs. Also subject to material processing and cooling techniques, further increases in turbine inlet gas temperature become increasingly difficult.
Referring to fig. 1, fig. 1 shows a thermodynamic cycle diagram of detonation pressure boost combustion (1-2-a-B-3-4), constant volume combustion (1-2-3-4) and constant pressure combustion (1-2-3B-4B), and as shown in the figure, the constant volume combustion cycle adopting the detonation pressure boost mode mainly comprises three steps: injecting fresh air and combustible gas, performing constant volume combustion, and removing high pressure waste to the turbine after finishing combustion. The cycle of detonation boost combustion is compared to a constant volume combustion cycle and a constant pressure combustion cycle without shock boost. Entropy increase is minimal and cycle work is maximal.
Disclosure of Invention
In order to overcome the defects of the prior art, the invention provides the single-rotor detonation supercharged aero-engine adopting a novel combustion mode, and the engine efficiency is improved on the premise of not increasing the gas temperature in front of a turbine by changing the thermodynamic cycle mode.
In order to achieve the purpose, the invention adopts the following technical scheme:
a detonation supercharged aero-engine is characterized by comprising a casing, a gas compressor, a gas inlet rotary valve, a detonation tube combustion chamber, a gas outlet rotary valve and a turbine, wherein the gas compressor, the gas inlet rotary valve, the detonation tube combustion chamber, the gas outlet rotary valve and the turbine are fixed in the casing; the top and the bottom of the detonation tube combustion chamber are respectively sealed by an air inlet rotary valve and an air outlet rotary valve, the compressor is arranged above the detonation tube combustion chamber, and the turbine is arranged below the detonation tube combustion chamber;
the gas inlet rotary valve is provided with a gas inlet, the gas outlet rotary valve is provided with a gas outlet, after the gas is pressurized by the gas compressor, pressurized air enters the detonation tube combustion chamber through the gas inlet of the gas inlet rotary valve for combustion, and then gas is discharged through the gas outlet of the gas outlet rotary valve and enters the turbine, and the gas inlet and the gas outlet are distributed in a staggered manner, so that the two ends of the inlet and the outlet of the gas are ensured to be sealed in the combustion process in the detonation tube combustion chamber;
the detonation tube combustion chamber comprises a plurality of detonation tubes, each detonation tube is fixed on the casing and is distributed in a radial circumferential array manner, a plurality of channels extending axially are formed in the detonation tube combustion chamber, and a fuel nozzle and an igniter are arranged on each detonation tube.
And the air inlet rotary valve and the air outlet rotary valve are respectively provided with a speed regulating device, and the rotating speed of the air inlet rotary valve and the rotating speed of the air outlet rotary valve are controlled according to the incoming flow speed in front.
The speed regulating device comprises an incoming flow state sensor, a rotor shaft rotating speed sensor, a control chip and an adjustable speed reducer; the incoming flow state sensor comprises an electronic gas speed measuring device and an electronic gas pressure measuring device, is positioned at the upstream of the air inlet rotary valve, can measure the air flow pressure and the air flow speed at the air inlet rotary valve under the current working condition, and converts the air flow pressure and the air flow speed into electric signals to be input into the control chip; the rotor shaft rotating speed sensor can measure the rotating speed of the rotor shaft under the current working condition, convert the rotating speed of the rotor shaft into an electric signal and input the electric signal into the control chip; the control chip calculates the optimal rotating speed of the rotary valve under the current working condition according to an input incoming flow state sensor electric signal based on a preset incoming flow state-rotary valve rotating speed curve, and calculates the optimal reduction ratio of the adjustable speed reducer according to the rotating speed of the rotor shaft, so as to generate a control signal for the adjustable speed reducer; the adjustable speed reducer is a mechanical speed changer with a servo actuator, an input shaft is connected to a rotor shaft, an output shaft is connected to a rotating shaft of the air inlet rotary valve (the speed reduction ratio is adjusted according to a control signal of the control chip), and the rotor shaft penetrates through the air compressor and the turbine along the central axis of the combustion chamber of the detonation tube.
Compared with the prior art, the invention has the beneficial effects that:
the temperature and the pressure of a combustion chamber of the engine are increased simultaneously through knocking and supercharging combustion, and the burden of the gas compressor is reduced on the premise of ensuring that the output power is unchanged, so that the weight of the gas compressor is reduced, the weight of the whole engine is reduced, and the thrust-weight ratio is improved. Compare in ripples rotor combustion chamber, fixed combustion chamber is more favorable to the distribution of ignition electric nozzle and fuel oil pipe, reduces the degree of difficulty of combustion chamber design.
Drawings
Fig. 1 is a schematic diagram of the principle of detonation-supercharged combustion, wherein a is a pressure-volume relationship diagram of a thermodynamic cycle process, and b is a temperature-entropy relationship diagram.
Fig. 2 is a schematic diagram of the structure of the knocking supercharged engine of the invention.
Figure 3 is a schematic view of a detonation tube combustion chamber single pass,
fig. 4 is a front view of the inlet and outlet rotary valves, wherein a is a schematic view of the combustion chamber inlet and inlet rotary valve interface and b is a schematic view of the combustion chamber outlet and outlet rotary valve interface.
FIG. 5 is a front view of an embodiment of a detonation tube combustion chamber having a total of 16 detonation tube combustion chambers.
In the figure: 1. a compressor; 2. an air inlet rotary valve; 3. a detonation tube combustion chamber; 4. an air outlet rotary valve; 5. a turbine; 6. a case; 7. a rotor shaft; 8. a speed regulating device. 31. A detonation tube; 32. a fuel nozzle; 33. an igniter.
Detailed Description
The present invention will be further described with reference to the following examples and drawings, but the scope of the present invention should not be limited thereto.
Referring to fig. 2, fig. 2 is a schematic structural diagram of the detonation supercharged engine of the present invention, and as shown in the figure, the detonation supercharged engine includes a compressor 1, an air inlet rotary valve 2, a detonation tube combustion chamber 3, an air outlet rotary valve 4, a turbine 5, a casing 6, a rotor shaft 7 and a speed regulation device 8.
The detonation tube combustion chamber 3 is composed of a plurality of detonation tubes 31, and each detonation tube 31 is provided with a fuel nozzle 32 and an igniter 33. In this embodiment, 16 detonation tubes 31 are fixed to the engine casing 6 and distributed in a radial circumferential array to form 16 channels extending axially along the detonation tube combustion chamber 3.
The air inlet rotary valve 2 is provided with an air inlet; the air outlet rotary valve 4 is provided with an air outlet, and the air inlet and the air outlet are distributed in a staggered manner, so that the inlet and the outlet of the gas are closed in the combustion process in the detonation tube. The inlet rotary valve 2 and the outlet rotary valve 4 are both provided with speed adjusting devices 8. The speed regulating device 8 controls the rotating speed of the air inlet rotary valve and the air outlet rotary valve according to the forward incoming flow speed, and ensures that gas is combusted in the detonation pipe 31 in a certain volume. The rotor shaft 7 passes through the center axis of the detonation tube combustion chamber 3.
After the gas is pressurized by the compressor 1, the pressurized air enters the detonation tube 31 through the air inlet of the air inlet rotary valve 2 in front of the detonation tube combustion chamber 3, is fully mixed with the oil mist sprayed by the fuel nozzle 32, and is subjected to constant volume combustion through the igniter 33. And then the gas is discharged from the gas outlet of the gas outlet rotary valve 4 and enters a turbine.
The compressor 1 of the present embodiment is a 4-stage compressor. The air inlet rotary valve 2 and the air outlet rotary valve 4 both adopt a sealing mode of combining a labyrinth sealing structure and an oil seal applied to an aircraft engine. The turbine 5 is a single stage turbine. The rotor shaft 7 is a single rotor shaft.
The detonation supercharged engine is a constant volume combustion process, can increase the pressure and the temperature of the combustion chamber simultaneously, is different from the constant volume combustion chamber in that the combustion process can produce compression waves, and can further promote the outlet pressure of the combustion chamber compared with the constant volume combustion chamber. The calculation result shows that: compared with the traditional constant-pressure combustion chamber, the cycle heat efficiency of the detonation supercharged engine can be improved by more than 20%, and the fuel consumption rate is reduced by more than 15% under the same thrust condition.
Claims (5)
1. The detonation supercharged aero-engine is characterized by comprising a casing (6), a gas compressor (1), a gas inlet rotary valve (2), a detonation tube combustion chamber (3), a gas outlet rotary valve (4) and a turbine (5), wherein the gas compressor (1), the gas inlet rotary valve (2), the detonation tube combustion chamber (3), the gas outlet rotary valve (4) and the turbine (5) are fixed in the casing (6); the top and the bottom of the detonation tube combustion chamber (3) are respectively sealed by an air inlet rotary valve (2) and an air outlet rotary valve (4), the air compressor (1) is arranged above the detonation tube combustion chamber (3), and the turbine (5) is arranged below the detonation tube combustion chamber;
the gas inlet rotary valve (2) on be equipped with the air inlet, the rotary valve (4) of giving vent to anger on be equipped with the gas outlet, gaseous process compressor (1) pressure boost after, pressurized air gets into detonation tube combustion chamber (3) internal combustion back through the air inlet of the rotary valve (2) that admits air, the process give vent to anger rotary valve (4) gas outlet exhaust gas and get into turbine (5), air inlet and gas outlet crisscross distribution, ensure that gaseous in the detonation tube combustion chamber (3) internal combustion in-process exit both ends are sealed.
2. The detonation-supercharged aero engine as claimed in claim 1, wherein said detonation tube combustion chamber (3) is comprised of a plurality of detonation tubes (31), each detonation tube (31) being fixed to said casing (6) and distributed in a radial circumferential array, a plurality of axially extending channels being formed in said detonation tube combustion chamber (3), each detonation tube (31) being provided with a fuel nozzle (32) and an igniter (33).
3. The detonation-supercharged aircraft engine of claim 1 or 2, characterized in that the inlet rotary valve (2) and the outlet rotary valve (4) are provided with speed regulating devices (8) for controlling the rotation speed of the inlet rotary valve and the outlet rotary valve according to the incoming flow speed.
4. The detonation-supercharged aircraft engine of claim 3, characterized in that said governor device (8) comprises an inflow condition sensor, a rotor shaft speed sensor, a control chip and an adjustable retarder; the incoming flow state sensor comprises an electronic gas speed measuring device and an electronic gas pressure measuring device, is positioned at the upstream of the air inlet rotary valve (2), can measure the air flow pressure and the air flow speed at the air inlet rotary valve (2) under the current working condition, and converts the air flow pressure and the air flow speed into electric signals to be input into the control chip; the rotor shaft rotating speed sensor can measure the rotating speed of the rotor shaft under the current working condition, convert the rotating speed of the rotor shaft into an electric signal and input the electric signal into the control chip; the control chip calculates the optimal rotating speed of the rotary valve under the current working condition according to an input incoming flow state sensor electric signal based on a preset incoming flow state-rotary valve rotating speed curve, and calculates the optimal reduction ratio of the adjustable speed reducer according to the rotating speed of the rotor shaft, so as to generate a control signal for the adjustable speed reducer; the adjustable speed reducer is a mechanical speed changer with a servo actuator, an input shaft is connected to a rotor shaft (7), an output shaft is connected to a rotating shaft of the air inlet rotary valve (2), and the speed reduction ratio is adjusted according to a control signal of the control chip.
5. The detonation-supercharged aeroengine of claim 4, characterized in that said rotor shaft (7) extends through said compressor (1) and turbine (5) along the central axis of said detonation tube combustion chamber (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111108196.2A CN113864050B (en) | 2021-09-22 | 2021-09-22 | Detonation supercharging aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111108196.2A CN113864050B (en) | 2021-09-22 | 2021-09-22 | Detonation supercharging aircraft engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113864050A true CN113864050A (en) | 2021-12-31 |
| CN113864050B CN113864050B (en) | 2023-02-10 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111108196.2A Active CN113864050B (en) | 2021-09-22 | 2021-09-22 | Detonation supercharging aircraft engine |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114526499A (en) * | 2022-01-12 | 2022-05-24 | 西北工业大学 | Two-phase pulse detonation combustion chamber based on rotating sliding arc ignition |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5901550A (en) * | 1993-04-14 | 1999-05-11 | Adroit Systems, Inc. | Liquid fueled pulse detonation engine with controller and inlet and exit valves |
| US20020139106A1 (en) * | 2001-03-29 | 2002-10-03 | Meholic Gregory Vincent | Rotary valve for pulse detonation engines |
| CA2681906A1 (en) * | 2009-10-08 | 2011-04-08 | General Electric Company | Plenum air preheat for cold startup of liquid-fueled pulse detonation engines |
| US20110126511A1 (en) * | 2009-11-30 | 2011-06-02 | General Electric Company | Thrust modulation in a multiple combustor pulse detonation engine using cross-combustor detonation initiation |
| CN106065830A (en) * | 2016-06-01 | 2016-11-02 | 南京航空航天大学 | A kind of pulse detonation combustor device based on rotary valve and pneumatic operated valve combination |
-
2021
- 2021-09-22 CN CN202111108196.2A patent/CN113864050B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5901550A (en) * | 1993-04-14 | 1999-05-11 | Adroit Systems, Inc. | Liquid fueled pulse detonation engine with controller and inlet and exit valves |
| US20020139106A1 (en) * | 2001-03-29 | 2002-10-03 | Meholic Gregory Vincent | Rotary valve for pulse detonation engines |
| CA2681906A1 (en) * | 2009-10-08 | 2011-04-08 | General Electric Company | Plenum air preheat for cold startup of liquid-fueled pulse detonation engines |
| US20110126511A1 (en) * | 2009-11-30 | 2011-06-02 | General Electric Company | Thrust modulation in a multiple combustor pulse detonation engine using cross-combustor detonation initiation |
| CN106065830A (en) * | 2016-06-01 | 2016-11-02 | 南京航空航天大学 | A kind of pulse detonation combustor device based on rotary valve and pneumatic operated valve combination |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114526499A (en) * | 2022-01-12 | 2022-05-24 | 西北工业大学 | Two-phase pulse detonation combustion chamber based on rotating sliding arc ignition |
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| Publication number | Publication date |
|---|---|
| CN113864050B (en) | 2023-02-10 |
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