RU2002100096A - The method of increasing the lifting force of the wing - Google Patents

The method of increasing the lifting force of the wing

Info

Publication number
RU2002100096A
RU2002100096A RU2002100096/28A RU2002100096A RU2002100096A RU 2002100096 A RU2002100096 A RU 2002100096A RU 2002100096/28 A RU2002100096/28 A RU 2002100096/28A RU 2002100096 A RU2002100096 A RU 2002100096A RU 2002100096 A RU2002100096 A RU 2002100096A
Authority
RU
Russia
Prior art keywords
increasing
lifting force
wing
engine
air
Prior art date
Application number
RU2002100096/28A
Other languages
Russian (ru)
Other versions
RU2240957C2 (en
Inventor
Владимир Леонидович Письменный
Original Assignee
Владимир Леонидович Письменный
Filing date
Publication date
Application filed by Владимир Леонидович Письменный filed Critical Владимир Леонидович Письменный
Priority to RU2002100096/11A priority Critical patent/RU2240957C2/en
Priority claimed from RU2002100096/11A external-priority patent/RU2240957C2/en
Publication of RU2002100096A publication Critical patent/RU2002100096A/en
Application granted granted Critical
Publication of RU2240957C2 publication Critical patent/RU2240957C2/en

Links

Claims (4)

1. Способ увеличения подъемной силы крыла, заключающийся в отборе воздуха с верхней поверхности крыла, отличающийся тем, что воздух отбирается более чем с 20% указанной поверхности через отверстия, которые соединены каналом (каналами) с компрессором (вентилятором) газотурбинного двигателя и образуют входное сечение воздухозаборника указанного двигателя.1. A method of increasing the lifting force of a wing, which consists in taking air from the upper surface of the wing, characterized in that air is taken from more than 20% of the indicated surface through openings that are connected by a channel (s) to a compressor (fan) of a gas turbine engine and form an inlet section the air intake of the specified engine. 2. Способ увеличения подъемной силы крыла по п.1, отличающийся тем, что отверстия имеют форму щелей.2. The method of increasing the lifting force of a wing according to claim 1, characterized in that the holes are in the form of slots. 3. Способ увеличения подъемной силы крыла по п.1, отличающийся тем, что отверстия расположены в несколько рядов.3. The method of increasing the lifting force of a wing according to claim 1, characterized in that the holes are arranged in several rows. 4. Способ увеличения подъемной силы крыла по п.1, отличающийся тем, что газотурбинный двигатель - двухконтурный турбореактивный двигатель.4. The method of increasing the lifting force of a wing according to claim 1, characterized in that the gas turbine engine is a dual-circuit turbojet engine.
RU2002100096/11A 2002-01-08 2002-01-08 Method for increasing of wing lift RU2240957C2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU2002100096/11A RU2240957C2 (en) 2002-01-08 2002-01-08 Method for increasing of wing lift

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU2002100096/11A RU2240957C2 (en) 2002-01-08 2002-01-08 Method for increasing of wing lift

Publications (2)

Publication Number Publication Date
RU2002100096A true RU2002100096A (en) 2003-09-20
RU2240957C2 RU2240957C2 (en) 2004-11-27

Family

ID=34309760

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2002100096/11A RU2240957C2 (en) 2002-01-08 2002-01-08 Method for increasing of wing lift

Country Status (1)

Country Link
RU (1) RU2240957C2 (en)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2539440C1 (en) * 2013-12-12 2015-01-20 Юлия Алексеевна Щепочкина Aircraft wing
RU2647363C2 (en) * 2016-09-12 2018-03-15 Владимир Дмитриевич Шкилев Method of regulating the lifting force of the aircraft

Similar Documents

Publication Publication Date Title
EP1505257A3 (en) Gas turbine blade circuit cooling
CA2528693C (en) Internally cooled gas turbine airfoil and method
US6837683B2 (en) Gas turbine engine aerofoil
EP1788194A3 (en) Methods and apparatus for cooling combustion turbine engine components
EP1600615A3 (en) Intercooler system for gas turbine engines
EP1731734A3 (en) Counterrotating turbofan engine
EP1363078A3 (en) Bulkhead panel for use in a combustion chamber of a gas turbine engine
EP1728990A3 (en) Auxiliary power unit supplied with air from the gas turbine
EP1548234A3 (en) Impingement baffle with embedded deflector
EP1674661A3 (en) Turbine airfoil cooling passageway
US6550254B2 (en) Gas turbine engine bleed scoops
EP1895140A3 (en) Fan exhaust nozzle for turbofan engine
EP1302628A3 (en) Airfoil with indentations to enhance heat transfer
EP1843099A3 (en) Gas turbine combustor and operating method
CN1840859A (en) Turbine airfoil with trailing edge convection
EP1467064A3 (en) Method and apparatus for cooling an airfoil
EP1712738A3 (en) Low solidity turbofan
EP1365154A3 (en) Counterrotatable booster compressor assembly for a gas turbine engine
RU2006122178A (en) COOLING CIRCUITS FOR WORKING BLADES OF GAS-TURBINE ENGINES
EP1586741A3 (en) Apparatus for damping vibrations of the stator vanes of a gas turbine engine
RU2006141862A (en) ADJUSTABLE TURBOJET ENGINE SHOVEL, TURBOJET ENGINE, GAS TURBINE ENGINE
EP1650407A3 (en) Method and apparatus for cooling gas turbine engines
EP1580417A3 (en) Noise suppression system for a gas turbine
US7137779B2 (en) Gas turbine airfoil leading edge cooling
EP1312756A3 (en) Blade for turbine engine