GB1439397A - Gas turbine unit - Google Patents

Gas turbine unit

Info

Publication number
GB1439397A
GB1439397A GB5236873A GB5236873A GB1439397A GB 1439397 A GB1439397 A GB 1439397A GB 5236873 A GB5236873 A GB 5236873A GB 5236873 A GB5236873 A GB 5236873A GB 1439397 A GB1439397 A GB 1439397A
Authority
GB
United Kingdom
Prior art keywords
compressor
turbine
machine
gas turbine
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
GB5236873A
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.)
ABB Stal AB
Original Assignee
Stal Laval Turbin AB
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 Stal Laval Turbin AB filed Critical Stal Laval Turbin AB
Publication of GB1439397A publication Critical patent/GB1439397A/en
Expired legal-status Critical Current

Links

Classifications

    • 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
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • 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
    • F02C9/20—Control of working fluid flow by throttling; by adjusting vanes
    • F02C9/22—Control of working fluid flow by throttling; by adjusting vanes by adjusting turbine vanes
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

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

Abstract

1439397 Gas turbine engines STAL-LAVAL TURBIN AB 12 Nov 1973 [13 Nov 1972] 52368/73 Heading F1G The invention relates to a gas turbine engine which comprises a compressor 3, a combustion chamber 4 and a turbine 5 which drives the compressor through a shaft; the turbine also drives a load 7. A rotary bladed machine 2 is disposed upstream of the compressor 3 and is provided with adjustable inlet guide vanes 1, the bladed rotor of the machine being connected to the shaft of the compressor/turbine assembly. The rotor blades of the machine are straight as shown at 8 Figs. 2a, 2b whereby the machine may operate either as a turbine Fig. 2a or as a compressor Fig. 2b depending on the setting of the inlet guide vanes 1. In the Figures vector c represents actual inlet velocity, u represents the rotor peripheral velocity and w the relative speed, the pressure side of the blade in Fig. 2a being the upper side, and in Fig. 2b the lower side.
GB5236873A 1972-11-13 1973-11-12 Gas turbine unit Expired GB1439397A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
SE14684/72A SE369093B (en) 1972-11-13 1972-11-13

Publications (1)

Publication Number Publication Date
GB1439397A true GB1439397A (en) 1976-06-16

Family

ID=20299487

Family Applications (1)

Application Number Title Priority Date Filing Date
GB5236873A Expired GB1439397A (en) 1972-11-13 1973-11-12 Gas turbine unit

Country Status (3)

Country Link
DE (1) DE2354490C3 (en)
GB (1) GB1439397A (en)
SE (1) SE369093B (en)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SE401710B (en) * 1976-09-24 1978-05-22 Kronogard Sven Olof GASTURBINE TRANSMISSION FACILITY
DE69016292T2 (en) * 1989-07-17 1995-09-07 Praxair Technology Inc Turbo expander with high efficiency.

Also Published As

Publication number Publication date
DE2354490A1 (en) 1974-05-16
DE2354490B2 (en) 1980-04-24
DE2354490C3 (en) 1981-01-08
SE369093B (en) 1974-08-05

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Legal Events

Date Code Title Description
PS Patent sealed
PCNP Patent ceased through non-payment of renewal fee