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GB1198515A - Deceleration Blade Lattice with Supersonic Inlet Velocity of the Fluid for the Rotor or Stator of a Turbomachine, such as a Compressor or Turbine. - Google Patents

Deceleration Blade Lattice with Supersonic Inlet Velocity of the Fluid for the Rotor or Stator of a Turbomachine, such as a Compressor or Turbine.

Info

Publication number
GB1198515A
GB1198515A GB33237/67A GB3323767A GB1198515A GB 1198515 A GB1198515 A GB 1198515A GB 33237/67 A GB33237/67 A GB 33237/67A GB 3323767 A GB3323767 A GB 3323767A GB 1198515 A GB1198515 A GB 1198515A
Authority
GB
United Kingdom
Prior art keywords
flow
region
turbine
deceleration
compressor
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
GB33237/67A
Inventor
Wilhelm Dettmering
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.)
Individual
Original Assignee
Individual
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 Individual filed Critical Individual
Publication of GB1198515A publication Critical patent/GB1198515A/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
    • F01D5/146—Shape, i.e. outer, aerodynamic form of blades with tandem configuration, split blades or slotted blades
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D21/00—Pump involving supersonic speed of pumped fluids
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/302—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor characteristics related to shock waves, transonic or supersonic flow
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S415/00—Rotary kinetic fluid motors or pumps
    • Y10S415/914—Device to control boundary layer

Landscapes

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

Abstract

1,198,515. Turbine and compressor blading. W. DETTMERING. July 19, 1967 [July 21, 1966], No.33237/67. Heading F1T. A deceleration blade lattice for supersonic inflow, for the rotor or stator of a turbo machine, such as an axial-flow compressor or turbine, comprises two inter-digitated rows of blades. The supersonic inflow is retarded to subsonic in region A by a normal shock wave stabilized by throttling. Thereafter, the flow is deflected in region B which is of substantially constant crosssection, and passes through regions C and D of constant or slightly divergent cross-section to a deceleration region E of divergent cross-section. The flow-path may be slightly deflected in the reverse direction in region D, as shown, to substantially equalize, by centrifugal effects, the pressures at point 2 and the directions of flow of the part-flows issuing from regions C and D. The discharge flow may be purely axial as shown or may include a peripheral component. In the embodiment of Fig. 3 (not shown), the deflecting and deceleration regions are both arranged in the downstream blade row, the blades of the upstream row being very thin and substantially straight with their leading edges each defining an included angle of about 6 degrees or less.
GB33237/67A 1966-07-21 1967-07-19 Deceleration Blade Lattice with Supersonic Inlet Velocity of the Fluid for the Rotor or Stator of a Turbomachine, such as a Compressor or Turbine. Expired GB1198515A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DED0050643 1966-07-21

Publications (1)

Publication Number Publication Date
GB1198515A true GB1198515A (en) 1970-07-15

Family

ID=7052807

Family Applications (1)

Application Number Title Priority Date Filing Date
GB33237/67A Expired GB1198515A (en) 1966-07-21 1967-07-19 Deceleration Blade Lattice with Supersonic Inlet Velocity of the Fluid for the Rotor or Stator of a Turbomachine, such as a Compressor or Turbine.

Country Status (3)

Country Link
US (1) US3442441A (en)
DE (1) DE1628237C3 (en)
GB (1) GB1198515A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108952823A (en) * 2017-05-22 2018-12-07 通用电气公司 Method and system for leading edge auxiliary blade
CN108952824A (en) * 2017-05-22 2018-12-07 通用电气公司 Method and system for leading edge auxiliary turbines stator blade

Families Citing this family (27)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3692425A (en) * 1969-01-02 1972-09-19 Gen Electric Compressor for handling gases at velocities exceeding a sonic value
DE1913028B1 (en) * 1969-03-14 1970-08-27 Dettmering Dr Ing Wilhelm Jet engine for high supersonic flow
US3837760A (en) * 1972-07-13 1974-09-24 Stalker Corp Turbine engine
US3861826A (en) * 1972-08-14 1975-01-21 Caterpillar Tractor Co Cascade diffuser having thin, straight vanes
GB1487324A (en) * 1973-11-15 1977-09-28 Rolls Royce Gas turbine engines
DE2515444B2 (en) * 1975-04-09 1977-05-18 Maschinenfabrik Augsburg-Nürnberg AG, 8500 Nürnberg LARGE CIRCLING SPEED FOR THERMAL, AXIAL-FLOW TURBINES
US4968216A (en) * 1984-10-12 1990-11-06 The Boeing Company Two-stage fluid driven turbine
US4859145A (en) * 1987-10-19 1989-08-22 Sundstrand Corporation Compressor with supercritical diffuser
JP2954539B2 (en) * 1996-08-09 1999-09-27 川崎重工業株式会社 Tandem cascade
US20030210980A1 (en) * 2002-01-29 2003-11-13 Ramgen Power Systems, Inc. Supersonic compressor
US7334990B2 (en) * 2002-01-29 2008-02-26 Ramgen Power Systems, Inc. Supersonic compressor
US7293955B2 (en) * 2002-09-26 2007-11-13 Ramgen Power Systrms, Inc. Supersonic gas compressor
US7434400B2 (en) * 2002-09-26 2008-10-14 Lawlor Shawn P Gas turbine power plant with supersonic shock compression ramps
TWI311611B (en) * 2006-08-25 2009-07-01 Ind Tech Res Inst Impeller structure and the centrifugal fan device using the same
WO2008060195A1 (en) * 2006-11-14 2008-05-22 Volvo Aero Corporation Vane assembly configured for turning a flow ina a gas turbine engine, a stator component comprising the vane assembly, a gas turbine and an aircraft jet engine
DE102009013399A1 (en) * 2009-03-16 2010-09-23 Mtu Aero Engines Gmbh Tandem blade design
CN101846100B (en) * 2009-03-24 2012-05-30 西北工业大学 Blade grid for improving pneumatic stability of gas compressor
JP6030853B2 (en) * 2011-06-29 2016-11-24 三菱日立パワーシステムズ株式会社 Turbine blade and axial turbine
US20130205795A1 (en) * 2012-02-09 2013-08-15 General Electric Company Turbomachine flow improvement system
EP2685050B1 (en) * 2012-07-11 2017-02-01 General Electric Technology GmbH Stationary vane assembly for an axial flow turbine
DE102014205226A1 (en) * 2014-03-20 2015-09-24 Rolls-Royce Deutschland Ltd & Co Kg Blade row group
DE102014206216B4 (en) * 2014-04-01 2016-12-29 Deutsches Zentrum für Luft- und Raumfahrt e.V. Compaction grating for an axial compressor
DE102014206217B4 (en) * 2014-04-01 2016-09-15 Deutsches Zentrum für Luft- und Raumfahrt e.V. Compaction grating for an axial compressor
US10094358B2 (en) * 2015-07-21 2018-10-09 Winnova Energy LLC Wind turbine blade with double airfoil profile
US10989219B2 (en) * 2019-02-04 2021-04-27 Honeywell International Inc. Diffuser assemblies for compression systems
CN110287647B (en) * 2019-07-18 2022-10-21 大连海事大学 A Design Method for Shock Wave Control of Planar Cascades of Transonic Compressors
WO2024096946A2 (en) 2022-08-11 2024-05-10 Next Gen Compression Llc Variable geometry supersonic compressor

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1771711A (en) * 1928-01-19 1930-07-29 Voith Gmbh J M Split guide blade for centrifugal pumps
US2839239A (en) * 1954-06-02 1958-06-17 Edward A Stalker Supersonic axial flow compressors
US2974927A (en) * 1955-09-27 1961-03-14 Elmer G Johnson Supersonic fluid machine
US3156407A (en) * 1958-07-07 1964-11-10 Commissariat Energie Atomique Supersonic compressors
FR1405388A (en) * 1964-05-14 1965-07-09 Hispano Suiza Sa Improvements made to supersonic compressors, in particular those of the centrifugal or axial-centrifugal type

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108952823A (en) * 2017-05-22 2018-12-07 通用电气公司 Method and system for leading edge auxiliary blade
CN108952824A (en) * 2017-05-22 2018-12-07 通用电气公司 Method and system for leading edge auxiliary turbines stator blade
US10883515B2 (en) 2017-05-22 2021-01-05 General Electric Company Method and system for leading edge auxiliary vanes
CN108952823B (en) * 2017-05-22 2021-01-26 通用电气公司 Method and system for leading edge auxiliary blade
US11002141B2 (en) 2017-05-22 2021-05-11 General Electric Company Method and system for leading edge auxiliary turbine vanes

Also Published As

Publication number Publication date
DE1628237A1 (en) 1970-08-27
DE1628237B2 (en) 1973-05-03
US3442441A (en) 1969-05-06
DE1628237C3 (en) 1973-11-22

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Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
PLNP Patent lapsed through nonpayment of renewal fees
PLNP Patent lapsed through nonpayment of renewal fees