US3724968A - Axial supersonic compressor - Google Patents

Axial supersonic compressor Download PDF

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Publication number
US3724968A
US3724968A US00127095A US12709571A US3724968A US 3724968 A US3724968 A US 3724968A US 00127095 A US00127095 A US 00127095A US 12709571 A US12709571 A US 12709571A US 3724968 A US3724968 A US 3724968A
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United States
Prior art keywords
blades
compressor
fixed
mobile
fluid
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Expired - Lifetime
Application number
US00127095A
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English (en)
Inventor
Jean-Marie Friberg
Pierre Maginot
Jean-Marie Merigoux
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.)
Alcatel CIT SA
Nokia Inc
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Nokia Inc
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Publication date
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Publication of US3724968A publication Critical patent/US3724968A/en
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    • 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
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • F04D29/544—Blade shapes
    • 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

Definitions

  • the present invention is directed to an axial supersonic fluid compressor that includes a fluid inlet opening followed by a cylindrical or conical divergent body portion extending downstream from the opening.
  • a centrally positioned cap is arranged in the inlet opening and is symmetrical'with respect to the axis of the compressor and with the cylindrical or conical body, defines a ring-shaped conduit.
  • At least one mobile wheel with thin deflecting blades is mounted on an axial engine shaft. The blades are attached downstream from the output of the mobile wheel in order partially to transform the kinetic energy of the pressurized fluid.
  • the channels or ducts of the mobile or fixed blades receive essentially normal shock waves at right angles to the flow passages between adjacent blades.
  • a supersonic axialcompressor receiving normal shock waves will give high compression rates with a reduced number of stages while still presenting an excellent power yield.
  • the supersonic axial compressor of the present invention is characterized by the fact that the angles of incidence upstream from the fixed and mobile blades have a relatively small height. Further, the passage cross section of the ducts between the blades of the mo bile wheel are convergent while the ducts between the fixed blades are divergent. The profile leading edges of the fixed and mobile blades are rounded off with a small radius of curvature. The angle of incidence between the fixed and mobile blades and the direction of fluid flow remains relatively small.
  • the passage cross sections of the ducts between the blades are divergent with respect to to the fixed blades and are convergent with respect to the mobile blades;
  • the ducts between the fixed blades are sufficiently short and divergent so that essentially straight shock waves will appear.
  • the ducts between the fixed blades have essentially slightly divergent passage crosssections with sufficient length so that a progressive flow transformation will be assured.
  • the ducts between the blades of the mobile wheel are sufficiently short and convergent so that essentially normal shock waves will occur.
  • the ducts between the blades of the mobile wheel have an essentially slightly convergent passage cross section and sufficient length so that progressive flow transformation will be realized.
  • the curvature radius of the profile of the leading edges of the fixed and the mobile blades is about 0.5 percentof the chord of the blade. This condition facilitates the obtaining of a stable shock wave with minimum losses.
  • the angles of the successive profiles of the blades have a reference direction, such that the product of the ratios of the relative fluid speed with respect to the blades at the critical speed of sound in the fluid, at the input and output of each stage of blades, will be unity. This condition tends to guarantee maximum power output.
  • the compressor contains a final slow down stage, having fixed blades subjected'to fluid at sub-sonic or supersonic speed.
  • the duct between the fixed blades has a straight cross section from the upstream toward the downstream direction so as to slow down the fluid to a moderate speed, for example, on the order of 0.25 Mach.
  • the compressor can incorporate in the final stage means for straightening the direction of the fluid where the means involves blades with staggered profiles which permit strong deviations with small losses in supersonic flow.
  • a supersonic axial compressor of the present invention can be advantageously used in a turbine engine, especially in an aircraft turbojet. In light turbojets, it can advantageously be followed by a likewise supersonic centrifugal compressor.
  • FIG. 1 discloses a schematic representation of the cross section of the compressor of the present inventron
  • FIG. 2 discloses the profiles of the blades of the distributor, the wheel and the compressor straightener.
  • FIG. 3 discloses in detail two neighboring blades of the mobile wheel.
  • FIGS. 1 and 2 The compressor disclosed in FIGS. 1 and 2 has a low sectional height comprising about 15 percent of the average radius. It includes a cylindrical inlet sleeve 1 and the cylindrical casing 2. In modified versions of the present invention, these envelopes may have a conical form. An axial cap 3, with the inlet sleeve 1 and the casing 2 limits the conduit offered for the air to be compressed. A shaft 4, connected to a motor or engine (not shown) drives the wheel 5.
  • the blades 8 and 8a of wheel have an inner surface which makes an angle of with the direction of incidence 12 of the inlet flow of air. Between the blades 8 and 8a a conduit or duct 13 is presented with a decreasing passage area cross section.
  • the leading edge 14 of blade will have a small radius of curvature, for example, 0.3mm for a blade whose chord is 65 mm.
  • the air penetrates between the blades of the wheel at a relative speed of Mach 1.35.
  • the deflection of the air, as it traverses the wheel is about 30.
  • the relative speed of the air at the output of the wheel is Mach 0.75.
  • the overall compression rate defined as the ratios of static pressure measured at a speed of Mach 0.25 in the downstream conduit 15 and the upstream conduit 16 of the compressor is 2.5.
  • the adiabatic yield of the complete stage, at this compression rate, is in excess of 0185.
  • a sub-sonic compressor with a single stage would only give a compression rate ofless than 1.5 for a similar yield.
  • the number of stages can be selected as a function of the final compression rate desired. Also it is possible to mix, into the gas flow coming from one stage, a secondary gas flow recycled at the same pressure and introduced by a tangential I3 inlet opening.
  • a supersonic axial flow fluid compressor comprising means defining a fluid inlet opening, including a cylindrical sleeve and an internally-mounted cap diverging in the downstream flow direction; a compressor housing; a mobile wheel rotatably mounted in said compressor housing, said mobile wheel having relatively thin pumping blades mounted thereon, said thin pumping blades having a leading and a trailing edge; means for rotatably driving the mobile wheel; distributing means including a plurality of fixed blades mounted in the fluid inlet opening upstream of the mobile wheel, said fixed blades having a leading edge and a trailing edge; a plurality of first fixed blades mounted downstream of the mobile wheel, each of said first fixed blades mounted downstream of said wheel having a leading edge and a trailing edge, the angles ofincidence of the fixed blades upstream and downstream of the mobile wheel and the blades of the mobile wheel with the direction of flow of fluid being relatively small within the range of 0-l 0", the cross-sectional thickness of the blades on the mobile wheel increasing in the direction of the
  • a compressor as in claim 6- further including means to slow the speed of the fluid including a second set of fixed blades mounted downstream of the first fixed blades.
  • a compressor as in claim 8 further including a supersonic centrifugal compressor connected in the air flow stream downstream of the second set of fixed blades.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Geometry (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Percussion Or Vibration Massage (AREA)
US00127095A 1970-03-23 1971-03-23 Axial supersonic compressor Expired - Lifetime US3724968A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR7010383A FR2083742A5 (enrdf_load_stackoverflow) 1970-03-23 1970-03-23

Publications (1)

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US3724968A true US3724968A (en) 1973-04-03

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Family Applications (1)

Application Number Title Priority Date Filing Date
US00127095A Expired - Lifetime US3724968A (en) 1970-03-23 1971-03-23 Axial supersonic compressor

Country Status (6)

Country Link
US (1) US3724968A (enrdf_load_stackoverflow)
DE (1) DE2113514C3 (enrdf_load_stackoverflow)
FR (1) FR2083742A5 (enrdf_load_stackoverflow)
GB (1) GB1299686A (enrdf_load_stackoverflow)
NO (1) NO138226C (enrdf_load_stackoverflow)
SE (1) SE376276B (enrdf_load_stackoverflow)

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3873229A (en) * 1973-12-26 1975-03-25 United Aircraft Corp Inlet guide vane configuration for noise control of supersonic fan
US4859145A (en) * 1987-10-19 1989-08-22 Sundstrand Corporation Compressor with supercritical diffuser
US5297930A (en) * 1991-12-31 1994-03-29 Cornell Research Foundation, Inc. Rotating stall suppression
US20030210980A1 (en) * 2002-01-29 2003-11-13 Ramgen Power Systems, Inc. Supersonic compressor
US20050013693A1 (en) * 2001-01-12 2005-01-20 Mitsubishi Heavy Industries Ltd. Blade structure in a gas turbine
US20050271500A1 (en) * 2002-09-26 2005-12-08 Ramgen Power Systems, Inc. Supersonic gas compressor
US20060021353A1 (en) * 2002-09-26 2006-02-02 Ramgen Power Systems, Inc. Gas turbine power plant with supersonic gas compressor
US20060034691A1 (en) * 2002-01-29 2006-02-16 Ramgen Power Systems, Inc. Supersonic compressor
EP2447538A3 (en) * 2010-10-28 2014-11-05 General Electric Company System and method of assembling a supersonic compressor system including a supersonic compressor rotor and a compressor assembly
US20140328675A1 (en) * 2013-05-03 2014-11-06 Techspace Aero S.A. Axial Turbomachine Stator with Ailerons at the Blade Roots
US20160208695A1 (en) * 2013-07-29 2016-07-21 John Charles Wells Gas turbine engine inlet
US20180156236A1 (en) * 2016-12-02 2018-06-07 Pratt & Whitney Canada Corp. Gas turbine engine bleed configuration
WO2021111432A1 (en) * 2019-12-02 2021-06-10 Bar Zohar Dan Nuclear fusion apparatus and method
US12066027B2 (en) 2022-08-11 2024-08-20 Next Gen Compression Llc Variable geometry supersonic compressor

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6206635B1 (en) * 1998-12-07 2001-03-27 Valeo, Inc. Fan stator
BE1026455B1 (fr) * 2018-07-09 2020-02-03 Safran Aero Boosters Sa Compresseur de turbomachine

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
IT459043A (enrdf_load_stackoverflow) *
US2435236A (en) * 1943-11-23 1948-02-03 Westinghouse Electric Corp Superacoustic compressor
US2623688A (en) * 1945-12-13 1952-12-30 Power Jets Res & Dev Ltd Rotary power conversion machine
US2628768A (en) * 1946-03-27 1953-02-17 Kantrowitz Arthur Axial-flow compressor
US2721693A (en) * 1949-05-24 1955-10-25 Onera (Off Nat Aerospatiale) Supersonic compressor
US2974927A (en) * 1955-09-27 1961-03-14 Elmer G Johnson Supersonic fluid machine
US3128939A (en) * 1964-04-14 Szydlowski

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
IT459043A (enrdf_load_stackoverflow) *
US3128939A (en) * 1964-04-14 Szydlowski
US2435236A (en) * 1943-11-23 1948-02-03 Westinghouse Electric Corp Superacoustic compressor
US2623688A (en) * 1945-12-13 1952-12-30 Power Jets Res & Dev Ltd Rotary power conversion machine
US2628768A (en) * 1946-03-27 1953-02-17 Kantrowitz Arthur Axial-flow compressor
US2721693A (en) * 1949-05-24 1955-10-25 Onera (Off Nat Aerospatiale) Supersonic compressor
US2974927A (en) * 1955-09-27 1961-03-14 Elmer G Johnson Supersonic fluid machine

Cited By (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3873229A (en) * 1973-12-26 1975-03-25 United Aircraft Corp Inlet guide vane configuration for noise control of supersonic fan
US4859145A (en) * 1987-10-19 1989-08-22 Sundstrand Corporation Compressor with supercritical diffuser
US5297930A (en) * 1991-12-31 1994-03-29 Cornell Research Foundation, Inc. Rotating stall suppression
US7229248B2 (en) * 2001-01-12 2007-06-12 Mitsubishi Heavy Industries, Ltd. Blade structure in a gas turbine
US20050013693A1 (en) * 2001-01-12 2005-01-20 Mitsubishi Heavy Industries Ltd. Blade structure in a gas turbine
US20050089403A1 (en) * 2001-01-12 2005-04-28 Mitsubishi Heavy Industries Ltd. Blade structure in a gas turbine
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
US20060034691A1 (en) * 2002-01-29 2006-02-16 Ramgen Power Systems, Inc. Supersonic compressor
US7293955B2 (en) 2002-09-26 2007-11-13 Ramgen Power Systrms, Inc. Supersonic gas compressor
US20060021353A1 (en) * 2002-09-26 2006-02-02 Ramgen Power Systems, Inc. Gas turbine power plant with supersonic gas compressor
US20050271500A1 (en) * 2002-09-26 2005-12-08 Ramgen Power Systems, Inc. Supersonic gas compressor
US7434400B2 (en) 2002-09-26 2008-10-14 Lawlor Shawn P Gas turbine power plant with supersonic shock compression ramps
EP2447538A3 (en) * 2010-10-28 2014-11-05 General Electric Company System and method of assembling a supersonic compressor system including a supersonic compressor rotor and a compressor assembly
US9739154B2 (en) * 2013-05-03 2017-08-22 Safran Aero Boosters Sa Axial turbomachine stator with ailerons at the blade roots
US20140328675A1 (en) * 2013-05-03 2014-11-06 Techspace Aero S.A. Axial Turbomachine Stator with Ailerons at the Blade Roots
US20160208695A1 (en) * 2013-07-29 2016-07-21 John Charles Wells Gas turbine engine inlet
US20180156236A1 (en) * 2016-12-02 2018-06-07 Pratt & Whitney Canada Corp. Gas turbine engine bleed configuration
WO2021111432A1 (en) * 2019-12-02 2021-06-10 Bar Zohar Dan Nuclear fusion apparatus and method
IL271106B1 (en) * 2019-12-02 2023-07-01 Bar Zohar Dan Device and method for nuclear fusion
IL271106B2 (en) * 2019-12-02 2023-11-01 Bar Zohar Dan Device and method for nuclear fusion
US12066027B2 (en) 2022-08-11 2024-08-20 Next Gen Compression Llc Variable geometry supersonic compressor
US12338829B2 (en) 2022-08-11 2025-06-24 Next Gen Compression Llc Variable geometry supersonic compressor

Also Published As

Publication number Publication date
NO138226B (no) 1978-04-17
SE376276B (enrdf_load_stackoverflow) 1975-05-12
DE2113514B2 (de) 1981-06-04
DE2113514A1 (de) 1971-10-14
NO138226C (no) 1978-08-02
FR2083742A5 (enrdf_load_stackoverflow) 1971-12-17
DE2113514C3 (de) 1982-02-25
GB1299686A (en) 1972-12-13

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