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RU2004111778A - TWO-CIRCUIT TURBOREACTIVE ENGINE MIXER (TRDD) - Google Patents

TWO-CIRCUIT TURBOREACTIVE ENGINE MIXER (TRDD) Download PDF

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Publication number
RU2004111778A
RU2004111778A RU2004111778/06A RU2004111778A RU2004111778A RU 2004111778 A RU2004111778 A RU 2004111778A RU 2004111778/06 A RU2004111778/06 A RU 2004111778/06A RU 2004111778 A RU2004111778 A RU 2004111778A RU 2004111778 A RU2004111778 A RU 2004111778A
Authority
RU
Russia
Prior art keywords
partitions
chevrons
circuit
trdd
passage
Prior art date
Application number
RU2004111778/06A
Other languages
Russian (ru)
Other versions
RU2265130C1 (en
Inventor
Николай Валерьевич Кирсанов (RU)
Николай Валерьевич Кирсанов
Рафаэль Касимович Тагиров (RU)
Рафаэль Касимович Тагиров
Original Assignee
Федеральное государственное унитарное предпри тие "Центральный институт авиационного моторостроени им. П.И. Баранова" (RU)
Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения им. П.И. Баранова"
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Федеральное государственное унитарное предпри тие "Центральный институт авиационного моторостроени им. П.И. Баранова" (RU), Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения им. П.И. Баранова" filed Critical Федеральное государственное унитарное предпри тие "Центральный институт авиационного моторостроени им. П.И. Баранова" (RU)
Priority to RU2004111778/06A priority Critical patent/RU2265130C1/en
Publication of RU2004111778A publication Critical patent/RU2004111778A/en
Application granted granted Critical
Publication of RU2265130C1 publication Critical patent/RU2265130C1/en

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Landscapes

  • Jet Pumps And Other Pumps (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (2)

1. Смеситель двухконтурного турбореактивного двигателя (ТРДД), содержащий сопло, обечайку, выходные кромки которой выполнены в виде шевронов, а за обечайкой находятся каналы для прохода газа и воздуха внутреннего и наружного контуров, отличающийся тем, что каналы образованы шевронами и двумя рядами чередующихся между собой перегородок, одни из которых являются плоскими, расположенными в плоскостях, проходящих через ось двигателя, а другие - изогнутыми, при этом выходные кромки изогнутых перегородок лежат в плоскости плоских перегородок и находятся ниже их по течению газа, причем канал для прохода воздуха наружного контура образован шевронами, перегородками и внутренней поверхностью сопла, а канал для прохода газа образован шевронами и перегородками.1. The mixer of a double-circuit turbojet engine (turbojet engine) containing a nozzle, a shell, the output edges of which are made in the form of chevrons, and behind the shell there are channels for the passage of gas and air of the internal and external circuits, characterized in that the channels are formed by chevrons and two rows alternating between partitions, one of which is flat, located in the planes passing through the axis of the engine, and others are curved, while the output edges of the curved partitions lie in the plane of the flat partitions and are located downstream of the gas, and the channel for the passage of air of the outer contour is formed by chevrons, partitions and the inner surface of the nozzle, and the channel for the passage of gas is formed by chevrons and partitions. 2. Смеситель по п.1, отличающийся тем, что плоские перегородки выполнены с изогнутым выходным участком.2. The mixer according to claim 1, characterized in that the flat partitions are made with a curved outlet section.
RU2004111778/06A 2004-04-20 2004-04-20 Mixer of bypass turbojet engine RU2265130C1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU2004111778/06A RU2265130C1 (en) 2004-04-20 2004-04-20 Mixer of bypass turbojet engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU2004111778/06A RU2265130C1 (en) 2004-04-20 2004-04-20 Mixer of bypass turbojet engine

Publications (2)

Publication Number Publication Date
RU2004111778A true RU2004111778A (en) 2005-10-10
RU2265130C1 RU2265130C1 (en) 2005-11-27

Family

ID=35850906

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2004111778/06A RU2265130C1 (en) 2004-04-20 2004-04-20 Mixer of bypass turbojet engine

Country Status (1)

Country Link
RU (1) RU2265130C1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2450150C2 (en) * 2007-02-12 2012-05-10 Снекма Пропюльсьон Солид Method for flap design manufacture of flow mixer made of composite material for gas turbine aircraft engine

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2310766C1 (en) * 2006-02-06 2007-11-20 Открытое акционерное общество "Авиадвигатель" Herringrone reaction nozzle of gas-turbine engine
FR2902836B1 (en) * 2006-06-26 2008-10-24 Snecma Sa HOOD FOR TURBOMACHINE TUBE WITH TRIANGULAR PATTERNS WITH INFLECTIVE POINT TO REDUCE JET NOISE
FR2902837B1 (en) * 2006-06-26 2008-10-24 Snecma Sa TURBOMACHINE TUBE HOOD WITH TRIANGULAR DOUBLE-SUMMIT PATTERNS TO REDUCE JET NOISE
FR2905734B1 (en) * 2006-09-07 2012-07-13 Airbus France DEVICE FOR ENHANCING THE EFFICIENCY OF ACOUSTIC TREATMENTS IN A CONDUIT OF AN AIRCRAFT ENGINE
FR2920036B1 (en) * 2007-08-14 2013-11-15 Airbus France ANTI-NOISE CHEVRONS FOR TUYERE
RU2728564C2 (en) * 2018-11-09 2020-07-31 Акционерное общество "Объединенная двигателестроительная корпорация" (АО"ОДК") Two-circuit two-shaft turbojet
RU210512U1 (en) * 2021-06-10 2022-04-18 Публичное Акционерное Общество "Одк-Сатурн" Petal mixer of a bypass turbojet engine

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA1100463A (en) * 1978-11-22 1981-05-05 Frederick L. Gilbertson Nozzle structure with notches
GB2207468A (en) * 1987-06-01 1989-02-01 Secr Defence Vortex silencing in gas turbine engines
US5381655A (en) * 1993-05-10 1995-01-17 General Electric Company Admission mixing duct assembly
RU2092708C1 (en) * 1993-09-07 1997-10-10 Центральный аэрогидродинамический институт им.проф.Н.Е.Жуковского Silencing nozzle of air-jet engine
US5638675A (en) * 1995-09-08 1997-06-17 United Technologies Corporation Double lobed mixer with major and minor lobes
US6360528B1 (en) * 1997-10-31 2002-03-26 General Electric Company Chevron exhaust nozzle for a gas turbine engine
AU2404000A (en) * 1999-01-04 2000-07-24 Allison Advanced Development Company Exhaust mixer and apparatus using same

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2450150C2 (en) * 2007-02-12 2012-05-10 Снекма Пропюльсьон Солид Method for flap design manufacture of flow mixer made of composite material for gas turbine aircraft engine

Also Published As

Publication number Publication date
RU2265130C1 (en) 2005-11-27

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Legal Events

Date Code Title Description
MM4A The patent is invalid due to non-payment of fees

Effective date: 20130421