GB1447144A - Gas turbine engine for subsonic flight - Google Patents

Gas turbine engine for subsonic flight

Info

Publication number
GB1447144A
GB1447144A GB502574A GB502574A GB1447144A GB 1447144 A GB1447144 A GB 1447144A GB 502574 A GB502574 A GB 502574A GB 502574 A GB502574 A GB 502574A GB 1447144 A GB1447144 A GB 1447144A
Authority
GB
United Kingdom
Prior art keywords
nozzle
gas turbine
turbine engine
area
subsonic flight
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.)
Expired
Application number
GB502574A
Other languages
English (en)
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
RTX Corp
Original Assignee
United Aircraft Corp
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 United Aircraft Corp filed Critical United Aircraft Corp
Publication of GB1447144A publication Critical patent/GB1447144A/en
Expired legal-status Critical Current

Links

Classifications

    • 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
    • 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
    • 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)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Control Of Turbines (AREA)
GB502574A 1973-02-08 1974-02-04 Gas turbine engine for subsonic flight Expired GB1447144A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US33079273A 1973-02-08 1973-02-08

Publications (1)

Publication Number Publication Date
GB1447144A true GB1447144A (en) 1976-08-25

Family

ID=23291354

Family Applications (1)

Application Number Title Priority Date Filing Date
GB502574A Expired GB1447144A (en) 1973-02-08 1974-02-04 Gas turbine engine for subsonic flight

Country Status (6)

Country Link
JP (1) JPS49111014A (enrdf_load_stackoverflow)
CA (1) CA986319A (enrdf_load_stackoverflow)
DE (1) DE2401212C2 (enrdf_load_stackoverflow)
FR (1) FR2217559B1 (enrdf_load_stackoverflow)
GB (1) GB1447144A (enrdf_load_stackoverflow)
IT (1) IT1007077B (enrdf_load_stackoverflow)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2236804A (en) * 1989-07-26 1991-04-17 Anthony Reginald Robins Compound nozzle
CN103987949A (zh) * 2011-12-07 2014-08-13 斯奈克玛 一种涡轮发动机的缩放喷嘴

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3044258A (en) * 1958-11-25 1962-07-17 Gen Electric Adjustable converging-diverging nozzle
US3520138A (en) * 1969-02-27 1970-07-14 United Aircraft Corp Convertible enginf

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2236804A (en) * 1989-07-26 1991-04-17 Anthony Reginald Robins Compound nozzle
CN103987949A (zh) * 2011-12-07 2014-08-13 斯奈克玛 一种涡轮发动机的缩放喷嘴
CN103987949B (zh) * 2011-12-07 2017-08-11 斯奈克玛 一种涡轮发动机的缩放喷嘴
RU2635863C2 (ru) * 2011-12-07 2017-11-16 Снекма Сужающееся-расширяющееся сопло турбомашины, двухконтурный турбореактивный двигатель и турбовинтовой двигатель

Also Published As

Publication number Publication date
IT1007077B (it) 1976-10-30
CA986319A (en) 1976-03-30
FR2217559A1 (enrdf_load_stackoverflow) 1974-09-06
DE2401212A1 (de) 1974-08-15
JPS49111014A (enrdf_load_stackoverflow) 1974-10-23
FR2217559B1 (enrdf_load_stackoverflow) 1977-08-19
DE2401212C2 (de) 1983-08-18

Similar Documents

Publication Publication Date Title
EP1402166A4 (en) THICKNESS REINFORCEMENT OF A ROCKET VEHICLE BY MEANS OF A DIVERGENT SECTION IN THE JET NOZZLE
GB745630A (en) Fluid flow control device for jet propulsion nozzles
GB1100099A (en) Improvements in convergent-divergent jet exhaust nozzle for supersonic aircraft
GB955518A (en) Thrust-reversal in turbo-jet devices
GB1198522A (en) Variable Area Propulsion Nozzle.
GB1194716A (en) Improved Base-Thrust Nozzles for Jet Propulsion Engines
GB1090147A (en) Thrust nozzle for supersonic gas turbine jet engines of the by-pass type
GB1296108A (enrdf_load_stackoverflow)
GB1038485A (en) Jet propulsion power plant
GB900040A (en) Exhaust nozzle with thrust deflector
GB1447144A (en) Gas turbine engine for subsonic flight
GB1127652A (en) A gas turbine jet propulsion engine afterburner
GB1370887A (en) Aircraft and gas turbine engines therefor
GB1117266A (en) Supersonic intake for a jet propulsion engine
GB894450A (en) Improvements in converging-diverging jet propulsion nozzle
GB1135377A (en) Improvements in or relating to exhaust units for jet propulsion units
GB1127653A (en) Improvements in and relating to a continuous fuel splash plate arrangement for a gas turbine jet propulsion engine afterburner
GB1114140A (en) Apparatus for maintaining continuity of a variable external contour of an adjustable jet pipe
GB1134996A (en) Jet noise suppressor in jet engine
US3157123A (en) Retro-nozzle
GB1324558A (en) Jet propulsion unit having a propellant gas jet deflector
GB1535598A (en) Turbofan aero engines and propulsion nozzles therefor
GB1383651A (en) Jet propulsion nozzles
HALL Experimental investigation of a novel VTOL thrust vectoring nozzle
FR2370862A1 (fr) Systeme de commande integre pour moteur a turbine a gaz

Legal Events

Date Code Title Description
PS Patent sealed
PCNP Patent ceased through non-payment of renewal fee