CN113756952A - Aircraft engine construction system integrating windlass lever principle - Google Patents
Aircraft engine construction system integrating windlass lever principle Download PDFInfo
- Publication number
- CN113756952A CN113756952A CN202110828378.0A CN202110828378A CN113756952A CN 113756952 A CN113756952 A CN 113756952A CN 202110828378 A CN202110828378 A CN 202110828378A CN 113756952 A CN113756952 A CN 113756952A
- Authority
- CN
- China
- Prior art keywords
- blade
- air
- lever principle
- stage
- semi
- 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.)
- Pending
Links
- 238000010276 construction Methods 0.000 title claims description 17
- 238000002485 combustion reaction Methods 0.000 claims abstract description 21
- 238000000034 method Methods 0.000 claims description 14
- 238000007906 compression Methods 0.000 claims description 8
- 230000006835 compression Effects 0.000 claims description 6
- 238000005516 engineering process Methods 0.000 claims description 4
- 230000001960 triggered effect Effects 0.000 claims description 4
- 238000005265 energy consumption Methods 0.000 claims description 2
- 230000001681 protective effect Effects 0.000 claims 1
- 239000000446 fuel Substances 0.000 abstract description 2
- 238000005507 spraying Methods 0.000 abstract 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000007547 defect Effects 0.000 description 1
- 210000005069 ears Anatomy 0.000 description 1
Classifications
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/10—Aircraft characterised by the type or position of power plants of gas-turbine type
-
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
-
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
-
- 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
-
- 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
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
-
- 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
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
-
- 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
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/03043—Convection cooled combustion chamber walls with means for guiding the cooling air flow
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Aviation & Aerospace Engineering (AREA)
- Wind Motors (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention provides an aircraft engine structure system integrating the lever principle of a windlass, which is mainly invented by independently dividing the combustion chambers of an original engine into three (or six) according to the air pressure and power principle and combining the lever principle of the windlass, then spraying the air to concave pocket type blades in a wheel annular semi-closed air chamber to drive air compressing blades to rotate around a shaft, simultaneously realizing air compressing and spraying, and maximizing the air pressure and power by less fuel consumption.
Description
Technical Field
The invention combines the principle of lever of the wheel according to the principle of air pressure and power, and utilizes the lever principle to furthest utilize the acting force formed by air pressure by the structural design of the obstacle. The technology belongs to the technical field of aircraft engines.
Background
With the deep research of the aircraft engine technology, the design of the original concave pocket type blade based on the air pressure dynamic principle is difficult to avoid various defects. There is therefore a problem of improving the utilization of such a pocket type blade.
Disclosure of Invention
According to the invention, three (or six) independent combustion chambers of self-contained gas collecting devices and a semi-closed wheel annular gas chamber are combined according to the principle of air pressure power, and concave pocket type blades are arranged inside the semi-closed wheel annular gas chamber and are connected with a motor shaft through a primary air compressor blade; the invention realizes the air pressure and power with less fuel consumption and maximum degree by combining the structure composition of a secondary air compressing blade, a tertiary air compressing blade, a spiral pipeline, a shaft tail cross-shaped fan-shaped blade and the like.
In one possible implementation, the aircraft engine construction system incorporating the windlass lever principle comprises: a self-contained combustion chamber and a semi-enclosed wheel annular plenum, the method comprising: three (or six) independent combustion chambers with self-contained gas collecting devices and semi-closed wheel annular gas chambers are respectively arranged from small to large according to the scale of thrust, the independent combustion chambers are respectively arranged on the outer edge of the engine at equal intervals, and nozzles of the combustion chambers are opposite to concave pocket type blades in the semi-closed wheel annular gas chambers. In one possible implementation, the aircraft engine construction system incorporating the windlass lever principle comprises: a concave pocket blade capable of implementing a first stage of compression, the method comprising: concave pocket type blades are distributed in the semi-closed wheel annular air chamber, each concave pocket type blade is connected with a shaft through a first stage air compression blade, and the concave pocket type blades are pushed to rotate around the shaft and drive the first stage air compression blades to rotate along with the fact that media in the combustion chamber are sprayed to the concave pocket type blades in the semi-closed wheel annular air chamber in the front direction. Meanwhile, the distribution pipeline inside the first-stage compressor blade is connected with the shaft, so that high-temperature gas can be conducted to the engine shaft, and the normal-temperature operation of the engine shaft is ensured.
In one possible implementation, the aircraft engine construction system incorporating the windlass lever principle comprises: a second stage compressor blade, the method comprising: the second stage air compressing blade and the first stage air compressing blade are designed in a reverse direction and are movable, and the second stage air compressing blade is connected with the tail cross-shaped fan-shaped turning blade through a shaft and drives the second stage air compressing blade to rotate in a reverse direction along with the ejection of tail gas of the airplane.
In one possible implementation, the aircraft engine construction system incorporating the windlass lever principle comprises: semi-closed wheel annular air chamber outer gas collecting device, the method includes: the semi-closed wheel annular air chamber is externally provided with a layer of small-caliber air collecting port and an air duct, because the cross section is small and dispersed, the whole air compression process does not participate in the combustion of the combustion chamber, and therefore accidents caused by foreign matter impact can be effectively avoided. In addition, the semi-closed wheel annular air chamber is influenced by a combustion high-temperature medium, so that the influence of severe weather such as ice, snow, heavy rain and the like on the gas collecting device can be effectively avoided.
In one possible implementation, the aircraft engine construction system incorporating the windlass lever principle comprises: an aircraft braking assistance apparatus, the method comprising: the inner wall of the tail part of the engine body is provided with a plurality of holes, the side of each hole is provided with an inner vertical baffle plate and an outer vertical baffle plate which are integrated into a whole and can rotate at 90 ℃ like ears, the vertical baffle plates are connected with the valves of the holes, when the landing gear of the airplane is contacted with the ground and the brake device is started, the valves of the holes in the inner wall of the tail part of the engine are triggered, and the air pressure switch is triggered to close the valves of the holes again after the landing gear of the airplane is contacted with the ground.
In one possible implementation, the aircraft engine construction system incorporating the windlass lever principle comprises: a third stage compressor blade, the method comprising: the third stage compressor blade rotates in the same direction as the first stage compressor blade under the action of the second stage compressor blade, the rotating speed depends on the air pressure generated by the rotation of the second stage compressor blade, and the pressurized air is changed in the moving direction through a spiral pipeline and is sprayed to the tail of the engine shaft through a cross-shaped fan-shaped blade connected with the second stage reverse compressor blade through the engine shaft, so that the second stage compressor blade is pushed to rotate reversely, and the air compressing task is completed. In a possible implementation mode, the principle of air pressure power is combined with the principle of a lever of a windlass, the combustion of an engine and the work of a pneumatic machine are distinguished through a modular design, and the most important function is to utilize the lever principle to eliminate the increased lever mass under the same condition so as to reduce the energy consumption in a certain proportion. The combination changes the prior art of space rocket launching, and realizes the technology of repeated reuse of space launching.
Various modifications and variations of the present invention may be made by those skilled in the art without departing from the spirit and scope of the present invention, but it is intended that the present invention also includes the modifications and variations if they come within the scope of the appended claims and their equivalents.
Claims (9)
1. An aircraft engine construction system combining the windlass lever principle is characterized by comprising the following components according to the air pressure power principle: three (or six) independent combustion chambers with self-contained gas collecting devices and a semi-closed wheel annular gas chamber, wherein concave pocket type blades are arranged inside the semi-closed wheel annular gas chamber and are connected with a motor shaft through a primary compressor blade; the combined structure of the two-stage compressor blade, the three-stage compressor blade, the spiral pipeline, the cross fan-shaped blade at the tail part of the shaft and the like.
2. An aircraft engine construction system incorporating the wheel lever principle according to claim 1 wherein: a self-contained combustion chamber and a semi-enclosed wheel annular plenum, the method comprising: three (or six) independent combustion chambers with self-contained gas collecting devices and semi-closed wheel annular gas chambers are respectively arranged from small to large according to the scale of thrust, the independent combustion chambers are respectively arranged on the outer edge of the engine at equal intervals, and nozzles of the combustion chambers are opposite to concave pocket type blades in the semi-closed wheel annular gas chambers.
3. An aircraft engine construction system incorporating the wheel lever principle according to claim 1 wherein: a concave pocket blade capable of implementing a first stage of compression, the method comprising: concave pocket type blades are distributed in the semi-closed wheel annular air chamber, each concave pocket type blade is connected with a shaft through a first stage air compression blade, and the concave pocket type blades are pushed to rotate around the shaft and drive the first stage air compression blades to rotate along with the fact that media in the combustion chamber are sprayed to the concave pocket type blades in the semi-closed wheel annular air chamber in the front direction. Meanwhile, the distribution pipeline inside the first-stage compressor blade is connected with the shaft, so that high-temperature gas can be conducted to the engine shaft, and the normal-temperature operation of the engine shaft is ensured.
4. An aircraft engine construction system incorporating the wheel lever principle according to claim 1 wherein: a second stage compressor blade, the method comprising: the second stage air compressing blade and the first stage air compressing blade are designed in a reverse direction and are movable, and the second stage air compressing blade is connected with the tail cross-shaped fan-shaped turning blade through a shaft and drives the second stage air compressing blade to rotate in a reverse direction along with the ejection of tail gas of the airplane.
5. An aircraft engine construction system incorporating the wheel lever principle according to claim 1 wherein: an external gas collection device of a semi-closed annular gas chamber, the method comprises the following steps: the semi-closed wheel annular air chamber is externally provided with a layer of small-caliber air collecting port and an air duct, because the cross section is small and dispersed, the whole air compression process does not participate in the combustion of the combustion chamber, and therefore accidents caused by foreign matter impact can be effectively avoided. In addition, the semi-closed wheel annular air chamber is influenced by a combustion high-temperature medium, so that the influence of severe weather such as ice, snow, heavy rain and the like on the gas collecting device can be effectively avoided.
6. An aircraft engine construction system incorporating the wheel lever principle according to claim 1 wherein: an aircraft braking assistance apparatus, the method comprising: the inner wall of the tail part of the engine body is provided with a plurality of holes, an inner and outer integrated upright baffle plate which can rotate at 90 ℃ is arranged beside the holes and is in ear shape, the upright baffle plate is connected with a valve of the holes, when the landing gear of the airplane is contacted with the ground and the brake device is started, the valve of the holes on the inner wall of the tail part of the engine is triggered, and the air pressure switch is triggered to close the valve of the holes again after the braking task is finished.
7. An aircraft engine construction system incorporating the wheel lever principle according to claim 1 wherein: a third stage compressor blade, the method comprising: the third stage compressor blade rotates in the same direction as the first stage compressor blade under the action of the second stage compressor blade, the rotating speed depends on the air pressure generated by the rotation of the second stage compressor blade, and the pressurized air is changed in the moving direction through a spiral pipeline and is sprayed to the tail of the engine shaft through a cross-shaped fan-shaped blade connected with the second stage reverse compressor blade through the engine shaft, so that the second stage compressor blade is pushed to rotate reversely, and the air compressing task is completed.
8. An aircraft engine construction system incorporating the wheel lever principle as claimed in claim 6 wherein the apertures in the inner wall of the engine are connected forwardly to the outer wall of the protective cover of the aircraft engine by means of ducting which simultaneously activates the valves at the base of the ducting to close and direct the reverse flow of air out of the apertures in the engine when the aircraft is being braked.
9. The aircraft engine construction system integrating the windlass lever principle of claim 1 is characterized in that the future spacecraft is the technology which is most likely to be used repeatedly to complete the space flight, the method comprises the air pressure power principle and the windlass lever principle, the combustion and the pneumatic machinery work of the engine are separated through the modular design, and the most important function is to utilize the lever principle to realize the proportional reduction of the energy consumption under the same condition. The method changes the prior art of launching the space rocket and also realizes repeated reuse of space launching.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110828378.0A CN113756952A (en) | 2019-08-23 | 2019-08-23 | Aircraft engine construction system integrating windlass lever principle |
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110828378.0A CN113756952A (en) | 2019-08-23 | 2019-08-23 | Aircraft engine construction system integrating windlass lever principle |
| CN201910781403.7A CN112412625A (en) | 2019-08-23 | 2019-08-23 | Novel aircraft engine system designed based on gas pressure dynamics principle |
Related Parent Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910781403.7A Division CN112412625A (en) | 2019-08-23 | 2019-08-23 | Novel aircraft engine system designed based on gas pressure dynamics principle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113756952A true CN113756952A (en) | 2021-12-07 |
Family
ID=74780323
Family Applications (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110828378.0A Pending CN113756952A (en) | 2019-08-23 | 2019-08-23 | Aircraft engine construction system integrating windlass lever principle |
| CN201910781403.7A Pending CN112412625A (en) | 2019-08-23 | 2019-08-23 | Novel aircraft engine system designed based on gas pressure dynamics principle |
Family Applications After (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910781403.7A Pending CN112412625A (en) | 2019-08-23 | 2019-08-23 | Novel aircraft engine system designed based on gas pressure dynamics principle |
Country Status (1)
| Country | Link |
|---|---|
| CN (2) | CN113756952A (en) |
Family Cites Families (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB644719A (en) * | 1947-05-14 | 1950-10-18 | Bataafsche Petroleum | Method of and apparatus for temporarily increasing the output of propulsive gases from a combustion chamber |
| CN2144181Y (en) * | 1992-12-03 | 1993-10-20 | 四川省万县地区电力公司 | Steam-gas turbine |
| EP1532358B1 (en) * | 2002-06-26 | 2013-02-27 | R-Jet Engineering Ltd. | Orbiting combustion nozzle engine |
| CN101825017B (en) * | 2005-05-23 | 2015-03-18 | 马同金 | Engine |
| US7743613B2 (en) * | 2006-11-10 | 2010-06-29 | General Electric Company | Compound turbine cooled engine |
| US20100058767A1 (en) * | 2008-09-05 | 2010-03-11 | General Electric Company | Swirl angle of secondary fuel nozzle for turbomachine combustor |
| JP6066065B2 (en) * | 2013-02-20 | 2017-01-25 | 三菱日立パワーシステムズ株式会社 | Gas turbine combustor with heat transfer device |
| CN103471135A (en) * | 2013-08-22 | 2013-12-25 | 邹吉武 | Jet-stream air suction and jet combustor |
| GB201406386D0 (en) * | 2014-04-09 | 2014-05-21 | Rolls Royce Plc | Gas turbine engine |
| US10317085B2 (en) * | 2016-02-25 | 2019-06-11 | General Electric Company | Combustor assembly |
| CN209892349U (en) * | 2019-05-27 | 2020-01-03 | 谢昌松 | Supercharged ramjet engine and aircraft |
-
2019
- 2019-08-23 CN CN202110828378.0A patent/CN113756952A/en active Pending
- 2019-08-23 CN CN201910781403.7A patent/CN112412625A/en active Pending
Also Published As
| Publication number | Publication date |
|---|---|
| CN112412625A (en) | 2021-02-26 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CA2440674C (en) | Airplane wheel unit and air jet unit | |
| US6672539B1 (en) | Power generation system | |
| CA2588214A1 (en) | Wind-powered pneumatic engine and a motor vehicle equipped with the engine | |
| EP0505509A4 (en) | Turbocraft | |
| CN101687544A (en) | Energy build-up aerodynamic braking method and device | |
| WO2006116907A1 (en) | Air compression aeroengine | |
| WO2014046564A1 (en) | Method for driving landing gear wheels of an aircraft and landing gear apparatus | |
| CN109821168B (en) | Variable-flow foam mixing and supplying system and fire fighting truck | |
| CN101450714A (en) | Jet type helicopters | |
| CN112644235A (en) | Medium aircraft driving system is striden to repeatedly discrepancy water | |
| US2728537A (en) | Aircraft with shrouded propelling and lifting rotors | |
| CN113756952A (en) | Aircraft engine construction system integrating windlass lever principle | |
| WO2021081616A1 (en) | Segmented augmented turbine assembly | |
| US3050007A (en) | Propeller apparatus | |
| CN103910069A (en) | Aircraft catapult driven by jet engine | |
| CN103623524A (en) | Strong wind smoke exhaust fire vehicle with air fan driven by aero-engine | |
| CN101144441A (en) | Turbine-rocket embedded type engine | |
| CN107745818A (en) | Aircraft propulsion system and vertical take-off and landing aircraft with same | |
| CN202970951U (en) | Turbojet engine | |
| CN201083164Y (en) | Turbine-rocket embedded type engine | |
| CN102515069B (en) | Air buoyancy lifting mover and transporting equipment employing same | |
| RU2567914C2 (en) | Aircraft with gas turbine engine provided with turbulence ejection propulsors | |
| KR20200073948A (en) | A Drone Aircraft | |
| CN220562969U (en) | Unmanned aerial vehicle of fire control that takes off and land perpendicularly of no oar formula | |
| CN220562940U (en) | Oil moves multistage axial-flow duct fan vertical take-off and landing system |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| DD01 | Delivery of document by public notice | ||
| DD01 | Delivery of document by public notice |
Addressee: Zhou Weiping Document name: Notification of qualification for preliminary examination of patent application for invention |
|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |