FR2417644A1 - Gas turbine ducted fan engine - has multistage axial flow compressor with initial stage over-pressurising, with excess fluid discharged via variable area ports into duct - Google Patents

Gas turbine ducted fan engine - has multistage axial flow compressor with initial stage over-pressurising, with excess fluid discharged via variable area ports into duct

Info

Publication number
FR2417644A1
FR2417644A1 FR7903259A FR7903259A FR2417644A1 FR 2417644 A1 FR2417644 A1 FR 2417644A1 FR 7903259 A FR7903259 A FR 7903259A FR 7903259 A FR7903259 A FR 7903259A FR 2417644 A1 FR2417644 A1 FR 2417644A1
Authority
FR
France
Prior art keywords
gas turbine
axial flow
duct
excess fluid
pressurising
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.)
Withdrawn
Application number
FR7903259A
Other languages
French (fr)
Inventor
Christopher John Smith
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Publication of FR2417644A1 publication Critical patent/FR2417644A1/en
Withdrawn legal-status Critical Current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

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The fan ducting is for a multi stage axial flow compressor (15) of a gas turbine engine. The upstream stage (30) of the compressor produces a higher pressure ratio than required by the remainder of the staging. The excess fluid, due to the'over-compression' is discharged through ports (29) in the compressor casing to enter the fan duct of the engine. The ports may be circumferential slot in the housing. The shell of the casing is movable on a linkage mechanism allowing the discharge port's cross-sectional area to be varied.
FR7903259A 1978-02-18 1979-02-08 Gas turbine ducted fan engine - has multistage axial flow compressor with initial stage over-pressurising, with excess fluid discharged via variable area ports into duct Withdrawn FR2417644A1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB655778 1978-02-18

Publications (1)

Publication Number Publication Date
FR2417644A1 true FR2417644A1 (en) 1979-09-14

Family

ID=9816675

Family Applications (1)

Application Number Title Priority Date Filing Date
FR7903259A Withdrawn FR2417644A1 (en) 1978-02-18 1979-02-08 Gas turbine ducted fan engine - has multistage axial flow compressor with initial stage over-pressurising, with excess fluid discharged via variable area ports into duct

Country Status (4)

Country Link
JP (1) JPS54126811A (en)
DE (1) DE2905818A1 (en)
FR (1) FR2417644A1 (en)
IT (1) IT1110502B (en)

Also Published As

Publication number Publication date
IT1110502B (en) 1985-12-23
JPS54126811A (en) 1979-10-02
DE2905818A1 (en) 1979-08-30
IT7919527A0 (en) 1979-01-23

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Legal Events

Date Code Title Description
ST Notification of lapse