GB901199A - Gas turbine - Google Patents

Gas turbine

Info

Publication number
GB901199A
GB901199A GB1528061A GB1528061A GB901199A GB 901199 A GB901199 A GB 901199A GB 1528061 A GB1528061 A GB 1528061A GB 1528061 A GB1528061 A GB 1528061A GB 901199 A GB901199 A GB 901199A
Authority
GB
United Kingdom
Prior art keywords
bores
fuel
atomizer
combustion chamber
radial
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
GB1528061A
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.)
BMW Triebwerkbau GmbH
Original Assignee
BMW Triebwerkbau GmbH
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 BMW Triebwerkbau GmbH filed Critical BMW Triebwerkbau GmbH
Publication of GB901199A publication Critical patent/GB901199A/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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • F01D11/04—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type using sealing fluid, e.g. steam
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16J—PISTONS; CYLINDERS; SEALINGS
    • F16J15/00—Sealings
    • F16J15/16—Sealings between relatively-moving surfaces
    • F16J15/40—Sealings between relatively-moving surfaces by means of fluid
    • F16J15/42—Sealings between relatively-moving surfaces by means of fluid kept in sealing position by centrifugal force
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
  • Nozzles (AREA)

Abstract

901,199. Gas turbine plant. BMW TRIEBWEBKBAU G.m.b.H. April 27, 1961 [April 30, 1960], No. 15280/61. Class 110 (3). A gas turbine engine comprises a centrifugal type compressor rotor 1 and an inward radial flow turbine rotor 2 disposed back to back with an annular combustion chamber 4 disposed therebetween, fuel being supplied to the combustion chamber by means of a centrifugal fuel atomizer 3 disposed between the compressor and turbine rotors so as to rotate therewith. The spaces between the combustion chamber and compressor and turbine rotors are sealed by means of rings of fuel formed centrifugally by fuel supplied to the atomizer. The fuel atomizer 3 is formed with one or more radial ducts 7 which is or are closed by plugs 6, transverse bores 8 communicating with the bores 7. The atomizer is also formed with further transverse bores 14 disposed at a greater radius than the bores 8, and further radial bores 15 communicate with the bores 14. The atomizer is formed with axially-extending flanges with which are associated flanged rings 9 so as to form annular chambers 10. Flanged baffles 12 project into the chambers 10. Fuel supplied through the shaft 5 flows through the radial bores 7, then through the transverse bores 8 into the annular chambers 10 where it forms as a result of centrifugal force into liquid rings 11. The fuel then discharges through the transverse bores 14 and radial bores 15 into the combustion chamber. The flanged baffles 12 project into the liquid rings 11.
GB1528061A 1960-04-30 1961-04-27 Gas turbine Expired GB901199A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DEB57677A DE1152850B (en) 1960-04-30 1960-04-30 Gas turbine, in particular small gas turbine

Publications (1)

Publication Number Publication Date
GB901199A true GB901199A (en) 1962-07-18

Family

ID=6971795

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1528061A Expired GB901199A (en) 1960-04-30 1961-04-27 Gas turbine

Country Status (2)

Country Link
DE (1) DE1152850B (en)
GB (1) GB901199A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2657205A (en) * 1950-01-09 1953-10-27 Hoechst Ag Dyes containing a vinyl sulfone
DE1261357B (en) * 1965-12-14 1968-02-15 Dornier Gmbh Gas turbine engine
US10731555B2 (en) 2015-06-01 2020-08-04 Samad Power Limited Micro-CHP gas fired boiler with gas turbine assembly

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19846976A1 (en) * 1998-10-12 2000-04-13 Bmw Rolls Royce Gmbh Fuel injection system for radial or slinger combustion chamber of small gas turbine with radial or diagonal compressor located in front of combustion chamber to which is connected turbine part via axially running rotor shaft

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2784551A (en) * 1951-06-01 1957-03-12 Orin M Raphael Vortical flow gas turbine with centrifugal fuel injection
DE1060193B (en) * 1954-09-10 1959-06-25 Henschel & Sohn Gmbh Rotating burner for combustion chambers of gas turbines

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2657205A (en) * 1950-01-09 1953-10-27 Hoechst Ag Dyes containing a vinyl sulfone
DE1261357B (en) * 1965-12-14 1968-02-15 Dornier Gmbh Gas turbine engine
US10731555B2 (en) 2015-06-01 2020-08-04 Samad Power Limited Micro-CHP gas fired boiler with gas turbine assembly

Also Published As

Publication number Publication date
DE1152850B (en) 1963-08-14

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