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GB1457634A - Converging-diverging supersonic nozzles - Google Patents

Converging-diverging supersonic nozzles

Info

Publication number
GB1457634A
GB1457634A GB1408874A GB1408874A GB1457634A GB 1457634 A GB1457634 A GB 1457634A GB 1408874 A GB1408874 A GB 1408874A GB 1408874 A GB1408874 A GB 1408874A GB 1457634 A GB1457634 A GB 1457634A
Authority
GB
United Kingdom
Prior art keywords
expansion
converging
passages
assembly
common
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
GB1408874A
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.)
Sohre J S
Original Assignee
Sohre J S
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 Sohre J S filed Critical Sohre J S
Publication of GB1457634A publication Critical patent/GB1457634A/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
    • F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
    • F01D5/143—Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
    • 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
    • F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
    • F01D1/02—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines
    • F01D1/04—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines traversed by the working-fluid substantially axially
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

1457634 Turbines J S SOHRE 29 March 1974 [21 May 1973] 14088/74 Heading F1T An assembly for supersonic expansion of a working fluid flowing to, or through, a turbine comprises a plurality of individual guide-members defining therebetween converging flow passages opening into a diverging expansion chamber common to at least two of the passages. In one arrangement, Fig, 2, 6, the assembly is formed by fixed nozzle vanes 20 defining converging passages 21 opening into a common diverging chamber 26 adjacent turbine rotor blades 24. The vanes 20 may extend to a limited degree into chamber 26 and some of them may be extended by partitions 36 to improve performance at offdesign conditions. In a further arrangement, Fig. 13, the converging flow passages are defined between turbine rotor blades 54 which open into a common expansion passage 70 defined between the rotor rim and a surrounding fixed or rotating shroud 72. A stator stage 80 is disposed between rotor stages 78, 82, all of the stages having a flow assembly as described. The invention enables standard nozzle blocks to be manufactured for co-operation with different sized expansion chambers for various expansion ratios. The invention is also applicable to radial flow turbines. The working fluid may be gas or steam.
GB1408874A 1973-05-21 1974-03-29 Converging-diverging supersonic nozzles Expired GB1457634A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US00362403A US3804335A (en) 1973-05-21 1973-05-21 Vaneless supersonic nozzle

Publications (1)

Publication Number Publication Date
GB1457634A true GB1457634A (en) 1976-12-08

Family

ID=23425992

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1408874A Expired GB1457634A (en) 1973-05-21 1974-03-29 Converging-diverging supersonic nozzles

Country Status (8)

Country Link
US (1) US3804335A (en)
JP (1) JPS508906A (en)
AU (1) AU6707274A (en)
CA (1) CA999527A (en)
DE (1) DE2417880A1 (en)
GB (1) GB1457634A (en)
IT (1) IT1004228B (en)
NL (1) NL7404887A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS58152106A (en) * 1982-03-05 1983-09-09 Nissan Motor Co Ltd Axial flow turbine

Families Citing this family (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3968935A (en) * 1973-05-21 1976-07-13 Sohre John S Contoured supersonic nozzle
GB1487324A (en) * 1973-11-15 1977-09-28 Rolls Royce Gas turbine engines
DE2435153B2 (en) * 1974-07-22 1977-06-30 Kraftwerk Union AG, 4330 Mülheim TURBO MACHINE, IN PARTICULAR STEAM TURBINE WITH HIGH STEAM INLET TEMPERATURE
JPS5314205A (en) * 1976-07-23 1978-02-08 Hitachi Ltd Step structure for axial-flow fluid machine
US4336039A (en) * 1977-10-13 1982-06-22 Sohre John S Geothermal turbine
USRE30720E (en) * 1978-07-12 1981-08-25 Contoured supersonic nozzle
ZA8234B (en) * 1981-01-05 1982-11-24 Alsthom Atlantique A turbine stage
JPH01259607A (en) * 1988-04-08 1989-10-17 Sharp Corp White noise waveform generating circuit
DE10303617A1 (en) * 2003-01-30 2004-10-07 GAT Gesellschaft für Antriebstechnik mbH Turbine wheel for driving rapidly rotating tools
GB9805030D0 (en) * 1998-03-11 1998-05-06 Rolls Royce Plc A stator vane assembly for a turbomachine
US6196793B1 (en) * 1999-01-11 2001-03-06 General Electric Company Nozzle box
US7238004B2 (en) * 1999-11-25 2007-07-03 Delta Electronics, Inc. Serial fan with a plurality of rotor vanes
DE10233199A1 (en) * 2002-07-22 2004-02-05 Dürr Systems GmbH Turbine motor of a rotary atomizer
FR2853929B1 (en) * 2003-04-17 2007-04-13 Alstom Switzerland Ltd STEAM TURBINE HAVING A HIGH PRESSURE BODY WITH A SINGLE FLOOR OF FINS
EP1790826A1 (en) * 2005-11-24 2007-05-30 Siemens Aktiengesellschaft Turbine vane for a turbine of a thermal power plant
US8230688B2 (en) * 2008-09-29 2012-07-31 Siemens Energy, Inc. Modular transvane assembly
US8276389B2 (en) * 2008-09-29 2012-10-02 Siemens Energy, Inc. Assembly for directing combustion gas
DE102009055180A1 (en) 2009-12-22 2011-06-30 Robert Bosch GmbH, 70469 Laval
EP2685050B1 (en) * 2012-07-11 2017-02-01 General Electric Technology GmbH Stationary vane assembly for an axial flow turbine
US9322335B2 (en) 2013-03-15 2016-04-26 Siemens Energy, Inc. Gas turbine combustor exit piece with hinged connections
DE102013218887A1 (en) * 2013-09-20 2015-03-26 Mahle International Gmbh Laval
US10677077B2 (en) * 2017-03-01 2020-06-09 Panasonic Corporation Turbine nozzle and radial turbine including the same
JP6866187B2 (en) * 2017-03-01 2021-04-28 パナソニック株式会社 Turbine nozzle and radial turbine equipped with it
JP6826574B2 (en) * 2018-09-26 2021-02-03 三菱重工マリンマシナリ株式会社 Partial feed turbine
BE1028108B1 (en) * 2020-02-28 2021-09-28 Safran Aero Boosters TURBOMACHINE TRANSSONIC COMPRESSOR

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB342289A (en) * 1929-10-18 1931-01-19 Gen Electric Co Ltd Improvements in elastic fluid turbines
US2378372A (en) * 1937-12-15 1945-06-12 Whittle Frank Turbine and compressor
US2258793A (en) * 1940-03-19 1941-10-14 Westinghouse Electric & Mfg Co Elastic-fluid turbine
GB615219A (en) * 1945-12-13 1949-01-04 Power Jets Res & Dev Ltd Improvements relating to rotary power conversion machines
US2702157A (en) * 1949-09-28 1955-02-15 Edward A Stalker Compressor employing radial diffusion
US2839239A (en) * 1954-06-02 1958-06-17 Edward A Stalker Supersonic axial flow compressors
US2953295A (en) * 1954-10-22 1960-09-20 Edward A Stalker Supersonic compressor with axially transverse discharge
US3744724A (en) * 1972-03-24 1973-07-10 Sulzer Ag Air distributing channel

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS58152106A (en) * 1982-03-05 1983-09-09 Nissan Motor Co Ltd Axial flow turbine

Also Published As

Publication number Publication date
IT1004228B (en) 1976-07-10
DE2417880A1 (en) 1974-12-12
AU6707274A (en) 1975-09-25
NL7404887A (en) 1974-11-25
US3804335A (en) 1974-04-16
CA999527A (en) 1976-11-09
JPS508906A (en) 1975-01-29

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Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
PCNP Patent ceased through non-payment of renewal fee