GB544909A - High speed propulsion plant - Google Patents

High speed propulsion plant

Info

Publication number
GB544909A
GB544909A GB407441A GB407441A GB544909A GB 544909 A GB544909 A GB 544909A GB 407441 A GB407441 A GB 407441A GB 407441 A GB407441 A GB 407441A GB 544909 A GB544909 A GB 544909A
Authority
GB
United Kingdom
Prior art keywords
turbine
rotors
jet propulsion
propulsion plant
compressor
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
GB407441A
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.)
Individual
Original Assignee
Individual
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 Individual filed Critical Individual
Priority to GB407441A priority Critical patent/GB544909A/en
Publication of GB544909A publication Critical patent/GB544909A/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
    • F02C3/067—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 having counter-rotating rotors
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for blades

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Combustion & Propulsion (AREA)
  • Materials Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

544,909. Jet propulsion plant. HEPPNER, F. A. M. March 26, 1941, No. 4074. [Class 114] [Also in Group XXVI] A gas turbine jet propulsion plant comprises air compressor and turbine of the oppositely running rotors type. The outer compressor blade discs 17 and turbine blade discs 19 are carried by a continuous rotary shell 13 which also encloses a combustion chamber 33 and is mounted on bearings 18, 20. The inner blade discs of both compressor and turbine are carried on a hollow shaft 15 mounted on a fixed shaft by bearings 22, 23. The exhaust of the turbine which is free of whirl is used for jet propulsion. The bladings are designed to give such different speeds to the outer and inner rotors as will neutralise gyroscopic effect. According to the Provisional Specification this difference of speeds may be controlled by means of a three part dynamo comprising a stator on the fixed shaft and rotors rotating with the inner and outer rotors of the gas turbine. This machine may be used for starting up. The turbine blades may have their leading edges covered with a hard metallic alloy and the Provisional Specification proposes the use of the metal known under the Registered Trade Mark "Stellite".
GB407441A 1941-03-26 1941-03-26 High speed propulsion plant Expired GB544909A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB407441A GB544909A (en) 1941-03-26 1941-03-26 High speed propulsion plant

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB407441A GB544909A (en) 1941-03-26 1941-03-26 High speed propulsion plant

Publications (1)

Publication Number Publication Date
GB544909A true GB544909A (en) 1942-05-01

Family

ID=9770244

Family Applications (1)

Application Number Title Priority Date Filing Date
GB407441A Expired GB544909A (en) 1941-03-26 1941-03-26 High speed propulsion plant

Country Status (1)

Country Link
GB (1) GB544909A (en)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1286331B (en) * 1964-10-23 1969-01-02 Rolls Royce Gas turbine engine
US20180209335A1 (en) * 2017-01-23 2018-07-26 General Electric Company Interdigitated counter rotating turbine system and method of operation
US20180209336A1 (en) * 2017-01-23 2018-07-26 General Electric Company Three spool gas turbine engine with interdigitated turbine section
US10539020B2 (en) * 2017-01-23 2020-01-21 General Electric Company Two spool gas turbine engine with interdigitated turbine section
US11428160B2 (en) 2020-12-31 2022-08-30 General Electric Company Gas turbine engine with interdigitated turbine and gear assembly
CN116379002A (en) * 2023-06-05 2023-07-04 中国空气动力研究与发展中心空天技术研究所 Design method of equal-rotation-speed reversing diffuser structure and diffuser structure

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1286331B (en) * 1964-10-23 1969-01-02 Rolls Royce Gas turbine engine
US20180209335A1 (en) * 2017-01-23 2018-07-26 General Electric Company Interdigitated counter rotating turbine system and method of operation
US20180209336A1 (en) * 2017-01-23 2018-07-26 General Electric Company Three spool gas turbine engine with interdigitated turbine section
US10539020B2 (en) * 2017-01-23 2020-01-21 General Electric Company Two spool gas turbine engine with interdigitated turbine section
US10544734B2 (en) * 2017-01-23 2020-01-28 General Electric Company Three spool gas turbine engine with interdigitated turbine section
US10655537B2 (en) * 2017-01-23 2020-05-19 General Electric Company Interdigitated counter rotating turbine system and method of operation
US11428160B2 (en) 2020-12-31 2022-08-30 General Electric Company Gas turbine engine with interdigitated turbine and gear assembly
CN116379002A (en) * 2023-06-05 2023-07-04 中国空气动力研究与发展中心空天技术研究所 Design method of equal-rotation-speed reversing diffuser structure and diffuser structure
CN116379002B (en) * 2023-06-05 2023-08-11 中国空气动力研究与发展中心空天技术研究所 Design method of equal-rotation-speed reversing diffuser structure and diffuser structure

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