GB745131A - Improvements in or relating to gas turbine engines having multi-stage axial-flow compressors - Google Patents

Improvements in or relating to gas turbine engines having multi-stage axial-flow compressors

Info

Publication number
GB745131A
GB745131A GB1415652A GB1415652A GB745131A GB 745131 A GB745131 A GB 745131A GB 1415652 A GB1415652 A GB 1415652A GB 1415652 A GB1415652 A GB 1415652A GB 745131 A GB745131 A GB 745131A
Authority
GB
United Kingdom
Prior art keywords
air
compressor
turbine
flow
rotor
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
GB1415652A
Inventor
Geoffrey Light Wilde
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
Priority to GB1415652A priority Critical patent/GB745131A/en
Publication of GB745131A publication Critical patent/GB745131A/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
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/06—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages

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

745,131. Gas turbine engines; axial-flow compressors. ROLLS-ROYCE. Ltd. May 21. 1953 [June 4. 1952], No. 14156/52. Classes 110(1) and 110(3) A gas turbine engine comprises a multi - stage axial - flow air compressor and one or more air turbine stages are arranged at the outlet of the compressor in series flow therewith, the turbine stages being adapted to produce a decrease in the axial velocity of the air, the air leaving the. air turbine being delivered to the combustion equipment of the engine. The air turbine is drivingly connected to the rotor of the air compressor. The compressor rotor has discs such as 13 and blades 112n and the compressor stator 10 has blades l1ln-1, 111n. The air turbine rotor 20 is mounted on the same shaft 21 as the compressor rotor discs and has blades 22, the air turbine casing portion 10a being sharply divergent. The object of the invention is to reduce the overall length of the engine by dispensing with the compressor diffuser. The air passage through the compressor is designed so that the air flow is of constant, increasing axial velocity. Specification 717,553 is referred to.
GB1415652A 1952-06-04 1952-06-04 Improvements in or relating to gas turbine engines having multi-stage axial-flow compressors Expired GB745131A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB1415652A GB745131A (en) 1952-06-04 1952-06-04 Improvements in or relating to gas turbine engines having multi-stage axial-flow compressors

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1415652A GB745131A (en) 1952-06-04 1952-06-04 Improvements in or relating to gas turbine engines having multi-stage axial-flow compressors

Publications (1)

Publication Number Publication Date
GB745131A true GB745131A (en) 1956-02-22

Family

ID=10036022

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1415652A Expired GB745131A (en) 1952-06-04 1952-06-04 Improvements in or relating to gas turbine engines having multi-stage axial-flow compressors

Country Status (1)

Country Link
GB (1) GB745131A (en)

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