US2601612A - Gas turbine motor of reduced - Google Patents

Gas turbine motor of reduced Download PDF

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Publication number
US2601612A
US2601612A US61286645A US2601612A US 2601612 A US2601612 A US 2601612A US 61286645 A US61286645 A US 61286645A US 2601612 A US2601612 A US 2601612A
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Prior art keywords
compressor
chambers
gas turbine
gas
reduced
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    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/46—Combustion chambers comprising an annular arrangement of several essentially tubular flame tubes within a common annular casing or within individual casings

Definitions

  • Gas turbine motors are particularly satisfactory from this point of view. Nevertheless the arrangement of the combustion chamber may cause an inconvenient increase in dimensions and the object of the present invention is to reduce this increase.
  • the combustion chamber is subdivided into several chambers connected in parallel between the compressor and the turbine and distributed around the axis of the motor or of the compressor.
  • Fig. 1 is a schematic view in section of a gas turbine motor of a known type.
  • Fig. 2 is an axial section of a motor in conf ormity with the invention.
  • Fig. 3 is a transverse section on line III-III of Fig. 2.
  • Figs. 4 and 5 are transverse sections of two modifications.
  • a gas turbine motor is constituted essentially, as shown in Fig. 1, by an air compressor C, by one or more combustion chambers Ch and by an expansion turbine T which is for example divided into two elements, one of which, Tc, controls the compressor, and the other of which, Tm, provides the motive power properly socalled.
  • the arrangement of the combustion chambers forming the subject of the present invention permits of housing the whole of the motor in a volume having a diameter as small as possible, whilst at the same time maintaining conditions which are necessary for the good operation of these chambers and comprising in particular:
  • a length of chamber sufficient for obtaining a combustion which is as complete as possible.
  • a double circulation, cold air outside-hot gas inside in such a way as to recuperate a maximum quantity of calories lost externally by convection and radiation.
  • This arrangement permits likewise of not puttin to Work the internal hot wall, the pressure being supported by the cold external wall.
  • the motor comprises a certain number of combustion chambers Ch disposed around the compressor.
  • These combustion chambers have cylindricalwalls in such a way as to obtain maximum lightness of the casing for a given pressure. They have double walls I, 2, the cold air coming from the compressor circulating externally of the chambers between the envelopes I and 2, the hot gases internally.
  • the burners or atomisers b disposed in the heads are particularly accessible and easy to inspect and to dismantle.
  • the length dimension being free within the limit of that of the compressor, a length necessary for the development of the flame and for complete combustion may easily be provided.
  • the external diameter of the turbine Ta necessary for driving the compressor being greater than the diameter of the compressor, the connection of such chambers at the inlet of the turbines is particularly favourable, and the external diameter may be equal to or only slightly greater than that of the turbines. From the point of view of expansion it is of interest that the chambers are connected to the compressor only by connecting tubes 3 supplying air under pressure, the chambers then being able to expand freely.
  • the chambers may be arranged only on a portion of a circle. which surrounds the compressor, or better on two oppositely disposed sectors, as illustrated in Fig. 5.
  • Fig. 4 relates to another particular construction of the invention comprising combustion chambers which have a lenticular cross-section in such a way as to obtain a very small volume with a moderate number of chambers.
  • combustion chambers which have a lenticular cross-section in such a way as to obtain a very small volume with a moderate number of chambers.
  • this disadvantage may be remedied by providing a connection between the different chambers by small bars 4.
  • the arrangement can still expand freely diametrically and lengthwise.
  • a gas turbine power plant comprising in combination an axial-flow multi-stage air compressor having a discharge passage, an axial-flow gas turbine coaxial with said compressor, adjacent thereto and adapted to drive same, said turbine having a gas-intake passage, the overall diameter of said turbine being greater than the over-all diameter of said compressor, and a plurality of separate, elongated combustion chambers of lenticular cross-section, each having an air inlet connected to said discharge passage and a gas outlet connected to' said gas-intake passage, said elongated chambers being located around said compressor, in the vicinity thereof, and extending in a direction substantially parallel to the axis of the compressor.
  • a gas turbine power plant comprising in combination an axial-flow multi-stage air compressor having a discharge passage, an axial-flow gas turbine coaxial with said compressor, adjacent thereto and. adapted to drive same, said turbine having a gas-intake passage, the over-all diameter of said turbine being greater than the over-all diameter of said compressor, and a plurality of separate, elongated combustion chambers, each including a tubular outer casing of lenticular cross-section connected at one end to said discharge passage and a tubular inner cas ing of lenticular cross-section inside said outer casing and spaced therefrom, connected at one end to said gas-intake passage, said ends being in the vicinity of one another, the combustion chamber being supported from said ends, the other ends of said outer casing and said inner casing being respectively closed and open, said elongated chambers being located around said compressor, in the vicinity thereof, and extending in a direction substantially parallel to the axis of the compressor.
  • a gas turbine power plant comprising in combination an air compressor having a discharge passage, a gas turbine coaxial with said compressor and adjacent thereto, said turbine having a gas-intake passage, and a pluralit of separate, elongated combustion chambers of lenticular cross-section, each having an air inlet connected to said discharge passage and a gas outlet connected to said gas-intake passage, said elongated chambers extending substantially parallel to the axis of the compressor.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US61286645 1942-01-08 1945-08-27 Gas turbine motor of reduced Expired - Lifetime US2601612A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US2601612TA 1942-01-08 1942-01-08

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US2601612A true US2601612A (en) 1952-06-24

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US61286645 Expired - Lifetime US2601612A (en) 1942-01-08 1945-08-27 Gas turbine motor of reduced

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US (1) US2601612A (ja)
GB (1) GB595286A (ja)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3365892A (en) * 1965-08-10 1968-01-30 Derderian George Turbomachine
EP2119966A1 (en) * 2008-05-15 2009-11-18 ALSTOM Technology Ltd Combustor with reduced carbon monoxide emissions
US20140137535A1 (en) * 2012-11-20 2014-05-22 General Electric Company Clocked combustor can array
US20170234541A1 (en) * 2012-10-23 2017-08-17 General Electric Technology Gmbh Burner for a can combustor

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1346509A (en) * 1918-09-14 1920-07-13 Ernst J Ohnell Explosion gas-turbine
GB347206A (en) * 1930-01-16 1931-04-16 Frank Whittle Improvements relating to the propulsion of aircraft and other vehicles
US2085761A (en) * 1933-02-15 1937-07-06 Milo Ab Aircraft power plant
US2256198A (en) * 1938-05-27 1941-09-16 Ernst Heinkel Aircraft power plant
US2326072A (en) * 1939-06-28 1943-08-03 Bbc Brown Boveri & Cie Gas turbine plant
US2332866A (en) * 1937-11-18 1943-10-26 Muller Max Adolf Combustion chamber for gas-flow engines
US2396068A (en) * 1941-06-10 1946-03-05 Youngash Reginald William Turbine
US2398654A (en) * 1940-01-24 1946-04-16 Anglo Saxon Petroleum Co Combustion burner
US2399046A (en) * 1940-03-26 1946-04-23 Gen Electric Gas turbine power plant
US2404334A (en) * 1939-12-09 1946-07-16 Power Jets Res & Dev Ltd Aircraft propulsion system and power unit

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1346509A (en) * 1918-09-14 1920-07-13 Ernst J Ohnell Explosion gas-turbine
GB347206A (en) * 1930-01-16 1931-04-16 Frank Whittle Improvements relating to the propulsion of aircraft and other vehicles
US2085761A (en) * 1933-02-15 1937-07-06 Milo Ab Aircraft power plant
US2332866A (en) * 1937-11-18 1943-10-26 Muller Max Adolf Combustion chamber for gas-flow engines
US2256198A (en) * 1938-05-27 1941-09-16 Ernst Heinkel Aircraft power plant
US2326072A (en) * 1939-06-28 1943-08-03 Bbc Brown Boveri & Cie Gas turbine plant
US2404334A (en) * 1939-12-09 1946-07-16 Power Jets Res & Dev Ltd Aircraft propulsion system and power unit
US2398654A (en) * 1940-01-24 1946-04-16 Anglo Saxon Petroleum Co Combustion burner
US2399046A (en) * 1940-03-26 1946-04-23 Gen Electric Gas turbine power plant
US2396068A (en) * 1941-06-10 1946-03-05 Youngash Reginald William Turbine

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3365892A (en) * 1965-08-10 1968-01-30 Derderian George Turbomachine
EP2119966A1 (en) * 2008-05-15 2009-11-18 ALSTOM Technology Ltd Combustor with reduced carbon monoxide emissions
US20090282830A1 (en) * 2008-05-15 2009-11-19 Adnan Eroglu Combustor with reduced carbon monoxide emissions
US7827777B2 (en) * 2008-05-15 2010-11-09 Alstom Technology Ltd. Combustor with reduced carbon monoxide emissions
US20170234541A1 (en) * 2012-10-23 2017-08-17 General Electric Technology Gmbh Burner for a can combustor
US10386073B2 (en) * 2012-10-23 2019-08-20 Ansaldo Energia Switzerland AG Burner for a can combustor
US10544939B2 (en) * 2012-10-23 2020-01-28 Ansaldo Energia Switzerland AG Burner for a can combustor
US20140137535A1 (en) * 2012-11-20 2014-05-22 General Electric Company Clocked combustor can array
JP2014102064A (ja) * 2012-11-20 2014-06-05 General Electric Co <Ge> 時計方向に旋回された燃焼器缶の配列
US9546601B2 (en) * 2012-11-20 2017-01-17 General Electric Company Clocked combustor can array

Also Published As

Publication number Publication date
GB595286A (ja) 1947-12-01

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