GB585345A - Internal-combustion turbine plant - Google Patents

Internal-combustion turbine plant

Info

Publication number
GB585345A
GB585345A GB1566242A GB1566242A GB585345A GB 585345 A GB585345 A GB 585345A GB 1566242 A GB1566242 A GB 1566242A GB 1566242 A GB1566242 A GB 1566242A GB 585345 A GB585345 A GB 585345A
Authority
GB
United Kingdom
Prior art keywords
blades
turbine
augmenter
compressor
carries
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
GB1566242A
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.)
Armstrong Siddeley Motors Ltd
Original Assignee
Armstrong Siddeley Motors Ltd
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 Armstrong Siddeley Motors Ltd filed Critical Armstrong Siddeley Motors Ltd
Priority to GB1566242A priority Critical patent/GB585345A/en
Publication of GB585345A publication Critical patent/GB585345A/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
    • 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
    • F02C3/073—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 the compressor and turbine stages being concentric

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

585,345. Gas turbines. ARMSTRONG SIDDELEY MOTORS, Ltd., and HEPPNER, F. A. M. Nov. 5, 1942, No. 15662. Drawings to Specification. [Class 110 (iii)] The inner blade rings of a contra-rotationa continuous combustion gas turbine are independently mounted and drive independently mounted stages of the air-compressor. The outer blade rings of the turbine are carried by a shell which also carries jet-augmenter blades. Several embodiments of this arrangement are described in a modification, the turbine blades of one direction of rotation are on the same rotor, discs as the compressor blades and are radially within the latter. The oppositelyrotating turbine blades are on discs carried by one shaft which also carries the rotating blades of the jet augmenter. Specifications 561,246, [Group XXXIV], and 585,340 are referred to.
GB1566242A 1942-11-05 1942-11-05 Internal-combustion turbine plant Expired GB585345A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB1566242A GB585345A (en) 1942-11-05 1942-11-05 Internal-combustion turbine plant

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1566242A GB585345A (en) 1942-11-05 1942-11-05 Internal-combustion turbine plant

Publications (1)

Publication Number Publication Date
GB585345A true GB585345A (en) 1947-02-05

Family

ID=10063179

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1566242A Expired GB585345A (en) 1942-11-05 1942-11-05 Internal-combustion turbine plant

Country Status (1)

Country Link
GB (1) GB585345A (en)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1190737B (en) * 1962-07-27 1965-04-08 Daimler Benz Ag Dual-circuit gas turbine jet engine
DE1190736B (en) * 1962-07-27 1965-04-08 Daimler Benz Ag Dual-circuit gas turbine jet engine
EP3056721A1 (en) * 2015-02-13 2016-08-17 United Technologies Corporation Turbine engine with a turbo-compressor
US10041408B2 (en) 2015-02-13 2018-08-07 United Technologies Corporation Turbine engine with a turbo-compressor
US10100731B2 (en) 2015-02-13 2018-10-16 United Technologies Corporation Turbine engine with a turbo-compressor
US10337401B2 (en) 2015-02-13 2019-07-02 United Technologies Corporation Turbine engine with a turbo-compressor

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1190737B (en) * 1962-07-27 1965-04-08 Daimler Benz Ag Dual-circuit gas turbine jet engine
DE1190736B (en) * 1962-07-27 1965-04-08 Daimler Benz Ag Dual-circuit gas turbine jet engine
EP3056721A1 (en) * 2015-02-13 2016-08-17 United Technologies Corporation Turbine engine with a turbo-compressor
US10041408B2 (en) 2015-02-13 2018-08-07 United Technologies Corporation Turbine engine with a turbo-compressor
US10100731B2 (en) 2015-02-13 2018-10-16 United Technologies Corporation Turbine engine with a turbo-compressor
US10125722B2 (en) 2015-02-13 2018-11-13 United Technologies Corporation Turbine engine with a turbo-compressor
US10337401B2 (en) 2015-02-13 2019-07-02 United Technologies Corporation Turbine engine with a turbo-compressor

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