GB605003A - Improvements in or relating to gas turbine plants - Google Patents

Improvements in or relating to gas turbine plants

Info

Publication number
GB605003A
GB605003A GB33505/45A GB3350545A GB605003A GB 605003 A GB605003 A GB 605003A GB 33505/45 A GB33505/45 A GB 33505/45A GB 3350545 A GB3350545 A GB 3350545A GB 605003 A GB605003 A GB 605003A
Authority
GB
United Kingdom
Prior art keywords
turbine
stage
compressor
segments
gas turbine
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
GB33505/45A
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.)
Rheinmetall Air Defence AG
Maschinenfabrik Oerlikon AG
Original Assignee
Werkzeugmaschinenfabrik Oerlikon Buhrle AG
Maschinenfabrik Oerlikon AG
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 Werkzeugmaschinenfabrik Oerlikon Buhrle AG, Maschinenfabrik Oerlikon AG filed Critical Werkzeugmaschinenfabrik Oerlikon Buhrle AG
Publication of GB605003A publication Critical patent/GB605003A/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
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/16—Control of working fluid flow
    • F02C9/18—Control of working fluid flow by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages

Landscapes

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

Abstract

605,003. Gas turbines. MASCHINENFABRIK OERLIKON. Dec. 11, 1945, No. 33505. Convention date, Jan. 27. Drawings to Specification. [Class 110 (iii)] In a continuous combustion gas turbine plant an additional expansion stage in a separate casing is introduced into the gas circuit for low loads. This stage may be a turbine on the admission side of the air-compressor or a turbine stage added in front of or behind the turbine. The stage may be provided with several separate admission segments, the number of segments in use being reduced as the low load decreases. The volume flow through the plant may be regulated by varying the area of the fixed passages in the compressor.
GB33505/45A 1945-01-27 1945-12-11 Improvements in or relating to gas turbine plants Expired GB605003A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH605003X 1945-01-27

Publications (1)

Publication Number Publication Date
GB605003A true GB605003A (en) 1948-07-14

Family

ID=4522992

Family Applications (1)

Application Number Title Priority Date Filing Date
GB33505/45A Expired GB605003A (en) 1945-01-27 1945-12-11 Improvements in or relating to gas turbine plants

Country Status (1)

Country Link
GB (1) GB605003A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3037345A (en) * 1956-05-07 1962-06-05 Sonnefeld Georg Gas turbine system with feedback cycle

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3037345A (en) * 1956-05-07 1962-06-05 Sonnefeld Georg Gas turbine system with feedback cycle

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