PL415184A1 - Dysza wylotowa dla silnika z turbiną gazową - Google Patents
Dysza wylotowa dla silnika z turbiną gazowąInfo
- Publication number
- PL415184A1 PL415184A1 PL415184A PL41518415A PL415184A1 PL 415184 A1 PL415184 A1 PL 415184A1 PL 415184 A PL415184 A PL 415184A PL 41518415 A PL41518415 A PL 41518415A PL 415184 A1 PL415184 A1 PL 415184A1
- Authority
- PL
- Poland
- Prior art keywords
- outer shell
- engine
- gas turbine
- trailing edge
- exhaust nozzle
- Prior art date
Links
Classifications
-
- 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
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/04—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
-
- 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
- B64D27/16—Aircraft characterised by the type or position of power plants of jet 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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/78—Other construction of jet pipes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
- F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
-
- 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
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
- F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
-
- 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
- F05D2250/00—Geometry
- F05D2250/10—Two-dimensional
- F05D2250/14—Two-dimensional elliptical
-
- 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
- F05D2250/00—Geometry
- F05D2250/10—Two-dimensional
- F05D2250/18—Two-dimensional patterned
- F05D2250/184—Two-dimensional patterned sinusoidal
-
- 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
- F05D2250/00—Geometry
- F05D2250/70—Shape
- F05D2250/75—Shape given by its similarity to a letter, e.g. T-shaped
-
- 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
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Urządzenie w postaci dyszy wylotowej silnika turbowentylatorowego, które obejmuje: osłonę wewnętrzną posiadającą centralną oś (12), przy czym ta osłona wewnętrzna jest umieszczona wewnątrz otaczającej osłony zewnętrznej, dla wyznaczania pierścieniowego kanału przepływu pomiędzy nimi, zakończonego wylotem przy krawędzi spływu osłony zewnętrznej, przy czym ta osłona wewnętrzna jest zakończona krawędzią spływu z tyłu wylotu; oraz pylon (14) przerywający obwodowo kanał; w którym tylna część osłony zewnętrznej nie jest osiowosymetryczna wokół wspólnej centralnej osi dyszy, a krawędź spływu osłony zewnętrznej jest pionowo nie współpłaszczyznowa.
Priority Applications (7)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
PL415184A PL415184A1 (pl) | 2015-12-10 | 2015-12-10 | Dysza wylotowa dla silnika z turbiną gazową |
BR102016027905-4A BR102016027905A2 (pt) | 2015-12-10 | 2016-11-28 | Turbofan exhaust nozzle machine |
EP16201720.6A EP3179083A1 (en) | 2015-12-10 | 2016-12-01 | Asymmetric exhaust nozzle for gas turbine engine |
JP2016233746A JP2017133497A (ja) | 2015-12-10 | 2016-12-01 | ガスタービンエンジンのための排気ノズル |
CA2950796A CA2950796A1 (en) | 2015-12-10 | 2016-12-06 | Exhaust nozzle for gas turbine engine |
US15/369,912 US20170166318A1 (en) | 2015-12-10 | 2016-12-06 | Exhaust nozzle for gas turbine engine |
CN201611129088.2A CN106870201A (zh) | 2015-12-10 | 2016-12-09 | 用于燃气涡轮发动机的排气喷嘴 |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
PL415184A PL415184A1 (pl) | 2015-12-10 | 2015-12-10 | Dysza wylotowa dla silnika z turbiną gazową |
Publications (1)
Publication Number | Publication Date |
---|---|
PL415184A1 true PL415184A1 (pl) | 2017-06-19 |
Family
ID=57471699
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PL415184A PL415184A1 (pl) | 2015-12-10 | 2015-12-10 | Dysza wylotowa dla silnika z turbiną gazową |
Country Status (7)
Country | Link |
---|---|
US (1) | US20170166318A1 (pl) |
EP (1) | EP3179083A1 (pl) |
JP (1) | JP2017133497A (pl) |
CN (1) | CN106870201A (pl) |
BR (1) | BR102016027905A2 (pl) |
CA (1) | CA2950796A1 (pl) |
PL (1) | PL415184A1 (pl) |
Families Citing this family (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102017115644A1 (de) * | 2017-07-12 | 2019-01-17 | Rolls-Royce Deutschland Ltd & Co Kg | Turbofantriebwerk |
GB201712340D0 (en) * | 2017-08-01 | 2017-09-13 | Rolls Royce Plc | Ducted fan gas turbine engine |
EP3750639A4 (en) | 2018-02-05 | 2021-04-28 | FUJIFILM Corporation | METHOD OF MANUFACTURING A RECORDED MEDIA, AND METHOD OF IMAGE RECORDING |
JP6692847B2 (ja) * | 2018-03-26 | 2020-05-13 | 三菱重工業株式会社 | ガスタービン燃焼器及びこれを備えたガスタービン機関 |
GB2575232A (en) * | 2018-04-20 | 2020-01-08 | Rolls Royce Plc | Turbofan engine |
GB201806426D0 (en) * | 2018-04-20 | 2018-06-06 | Rolls Royce Plc | Turbofan engine |
GB2575811A (en) * | 2018-07-23 | 2020-01-29 | Airbus Operations Ltd | Aircraft engine nacelle |
KR102438864B1 (ko) * | 2018-09-28 | 2022-08-31 | 램 리써치 코포레이션 | 플라즈마 챔버의 전극으로 전력 전달 최적화를 위한 방법들 및 시스템들 |
GB201820925D0 (en) | 2018-12-21 | 2019-02-06 | Rolls Royce Plc | Turbine engine |
US11204037B2 (en) | 2018-12-21 | 2021-12-21 | Rolls-Royce Plc | Turbine engine |
GB201820919D0 (en) | 2018-12-21 | 2019-02-06 | Rolls Royce Plc | Turbine engine |
GB201820924D0 (en) | 2018-12-21 | 2019-02-06 | Rolls Royce Plc | Turbine engine |
GB201820922D0 (en) * | 2018-12-21 | 2019-02-06 | Rolls Royce Plc | Turbine Engine |
Family Cites Families (24)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1080A (en) * | 1839-02-13 | Improvement in self-acting temples for looms | ||
US53997A (en) * | 1866-04-17 | Improved foot-scraper | ||
US3806067A (en) * | 1971-08-30 | 1974-04-23 | Gen Electric | Area ruled nacelle |
US5369954A (en) * | 1991-04-22 | 1994-12-06 | General Electric Company | Turbofan engine bypass and exhaust system |
FR2896772B1 (fr) * | 2006-01-27 | 2008-04-25 | Snecma Sa | Systeme d' ejection d'un turboreacteur a double flux |
US7669785B2 (en) * | 2006-04-24 | 2010-03-02 | The Boeing Company | Integrated engine exhaust systems and methods for drag and thermal stress reduction |
US8157207B2 (en) * | 2006-08-09 | 2012-04-17 | The Boeing Company | Jet engine nozzle exit configurations, including projections oriented relative to pylons, and associated systems and methods |
US7966824B2 (en) * | 2006-08-09 | 2011-06-28 | The Boeing Company | Jet engine nozzle exit configurations and associated systems and methods |
US7520124B2 (en) * | 2006-09-12 | 2009-04-21 | United Technologies Corporation | Asymmetric serrated nozzle for exhaust noise reduction |
US8123470B2 (en) * | 2007-08-10 | 2012-02-28 | Honeywell International Inc. | Turbine assembly with semi-divided nozzle and half-collar piston |
US9701415B2 (en) * | 2007-08-23 | 2017-07-11 | United Technologies Corporation | Gas turbine engine with axial movable fan variable area nozzle |
US9181899B2 (en) * | 2008-08-27 | 2015-11-10 | General Electric Company | Variable slope exhaust nozzle |
US8959889B2 (en) * | 2008-11-26 | 2015-02-24 | The Boeing Company | Method of varying a fan duct nozzle throat area of a gas turbine engine |
US8127532B2 (en) * | 2008-11-26 | 2012-03-06 | The Boeing Company | Pivoting fan nozzle nacelle |
US9057286B2 (en) * | 2010-03-30 | 2015-06-16 | United Technologies Corporation | Non-circular aft nacelle cowling geometry |
US9022311B2 (en) * | 2010-08-20 | 2015-05-05 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Active aircraft pylon noise control system |
US20140083079A1 (en) * | 2012-09-26 | 2014-03-27 | United Technologies Corporation | Geared turbofan primary and secondary nozzle integration geometry |
EP2971727B1 (en) * | 2013-03-15 | 2018-04-11 | United Technologies Corporation | Asymmetric fan nozzle in high-bpr separate-flow nacelle |
US9732700B2 (en) * | 2013-10-24 | 2017-08-15 | The Boeing Company | Methods and apparatus for passive thrust vectoring and plume deflection |
US9546618B2 (en) * | 2013-10-24 | 2017-01-17 | The Boeing Company | Methods and apparatus for passive thrust vectoring and plume deflection |
US20150330254A1 (en) * | 2014-05-15 | 2015-11-19 | United Technologies Corporation | Compact Nacelle With Contoured Fan Nozzle |
US10001080B2 (en) * | 2014-08-19 | 2018-06-19 | The Boeing Company | Thrust reverse variable area fan nozzle |
GB201420010D0 (en) * | 2014-11-11 | 2014-12-24 | Rolls Royce Plc | Gas turbine engine |
US9810178B2 (en) * | 2015-08-05 | 2017-11-07 | General Electric Company | Exhaust nozzle with non-coplanar and/or non-axisymmetric shape |
-
2015
- 2015-12-10 PL PL415184A patent/PL415184A1/pl unknown
-
2016
- 2016-11-28 BR BR102016027905-4A patent/BR102016027905A2/pt not_active Application Discontinuation
- 2016-12-01 EP EP16201720.6A patent/EP3179083A1/en not_active Withdrawn
- 2016-12-01 JP JP2016233746A patent/JP2017133497A/ja active Pending
- 2016-12-06 US US15/369,912 patent/US20170166318A1/en not_active Abandoned
- 2016-12-06 CA CA2950796A patent/CA2950796A1/en not_active Abandoned
- 2016-12-09 CN CN201611129088.2A patent/CN106870201A/zh active Pending
Also Published As
Publication number | Publication date |
---|---|
JP2017133497A (ja) | 2017-08-03 |
CA2950796A1 (en) | 2017-06-10 |
CN106870201A (zh) | 2017-06-20 |
EP3179083A1 (en) | 2017-06-14 |
BR102016027905A2 (pt) | 2017-12-05 |
US20170166318A1 (en) | 2017-06-15 |
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