PL415184A1 - Dysza wylotowa dla silnika z turbiną gazową - Google Patents

Dysza wylotowa dla silnika z turbiną gazową

Info

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
Application number
PL415184A
Other languages
English (en)
Inventor
Gavin Joseph Holt
Tomasz Iglewski
John Robert Holland
Original Assignee
General Electric Company
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 General Electric Company filed Critical General Electric Company
Priority to PL415184A priority Critical patent/PL415184A1/pl
Priority to BR102016027905-4A priority patent/BR102016027905A2/pt
Priority to EP16201720.6A priority patent/EP3179083A1/en
Priority to JP2016233746A priority patent/JP2017133497A/ja
Priority to CA2950796A priority patent/CA2950796A1/en
Priority to US15/369,912 priority patent/US20170166318A1/en
Priority to CN201611129088.2A priority patent/CN106870201A/zh
Publication of PL415184A1 publication Critical patent/PL415184A1/pl

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.
PL415184A 2015-12-10 2015-12-10 Dysza wylotowa dla silnika z turbiną gazową PL415184A1 (pl)

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)

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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

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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
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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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