GB1484614A - Noise suppression for gas turbine engines - Google Patents

Noise suppression for gas turbine engines

Info

Publication number
GB1484614A
GB1484614A GB50543/74A GB5054374A GB1484614A GB 1484614 A GB1484614 A GB 1484614A GB 50543/74 A GB50543/74 A GB 50543/74A GB 5054374 A GB5054374 A GB 5054374A GB 1484614 A GB1484614 A GB 1484614A
Authority
GB
United Kingdom
Prior art keywords
fan
reflecting surface
gas turbine
vector
blades
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
GB50543/74A
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.)
Raytheon Technologies Corp
Original Assignee
United Aircraft Corp
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 United Aircraft Corp filed Critical United Aircraft Corp
Publication of GB1484614A publication Critical patent/GB1484614A/en
Expired legal-status Critical Current

Links

Classifications

    • 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
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/663—Sound attenuation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F02C7/045—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for noise suppression
    • 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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Abstract

1484614 Gas turbine ducted fan engines; noise suppression UNITED AIRCRAFT CORP 21 Nov 1974 [26 Dec 1973] 50543/74 Headings F1C F1G and F1J The invention relates to a gas turbine engine having a row of stationary inlet guide vanes and downstream thereof a supersonic rotor such as a fan rotor in the case of a gas turbine ducted fan engine. The inlet guide vanes are indicated at 16 and comprise a forward face 18 which is directed oppositely to the direction of rotation 29 of the fan rotor, the fan rotor blades being indicated at 22. The flow of air into the fan blades 22 is supersonic at design speed. The forward face 18 of each IGV 16 comprises a reflecting surface 26 and a tangential line to each point on the reflecting surface is such that it forms a downstream angle equal to or greater than 90 degrees with a line DB parallel to the direction of noise propagation at each respective point on the reflecting surface. The relative flow of air into the fan blades 22 is supersonic, the blades generate shock waves 24 which travel at a speed and direction represented by vector DA which may be regarded as being normal to the shock waves 24. Air entering the IGV's as indicated by arrow 28 is discharged therefrom in a direction and at a velocity represented by vector AB, the direction being substantially parallel to the reflecting surface 26. The sum of the vectors DA and AB is vector DB and the direction of this vector is referred to as the "direction of noise propagation". A line FE is drawn through the trailing edge 27 of an adjacent IGV, the point E being the upstream limit of the reflecting surface 26. Thus any noise propagated in the direction DB is reflected back towards the fan and does not pass forwardly out of the engine.
GB50543/74A 1973-12-26 1974-11-21 Noise suppression for gas turbine engines Expired GB1484614A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US427871A US3873229A (en) 1973-12-26 1973-12-26 Inlet guide vane configuration for noise control of supersonic fan

Publications (1)

Publication Number Publication Date
GB1484614A true GB1484614A (en) 1977-09-01

Family

ID=23696620

Family Applications (1)

Application Number Title Priority Date Filing Date
GB50543/74A Expired GB1484614A (en) 1973-12-26 1974-11-21 Noise suppression for gas turbine engines

Country Status (4)

Country Link
US (1) US3873229A (en)
CA (1) CA1000207A (en)
FR (1) FR2256315B3 (en)
GB (1) GB1484614A (en)

Families Citing this family (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4131387A (en) * 1976-02-27 1978-12-26 General Electric Company Curved blade turbomachinery noise reduction
US6655917B1 (en) * 2000-10-17 2003-12-02 Sun Microsystems, Inc. Method and apparatus for serial coolant flow control
US6386830B1 (en) * 2001-03-13 2002-05-14 The United States Of America As Represented By The Secretary Of The Navy Quiet and efficient high-pressure fan assembly
US7334990B2 (en) * 2002-01-29 2008-02-26 Ramgen Power Systems, Inc. Supersonic compressor
US20030210980A1 (en) * 2002-01-29 2003-11-13 Ramgen Power Systems, Inc. Supersonic compressor
US7434400B2 (en) * 2002-09-26 2008-10-14 Lawlor Shawn P Gas turbine power plant with supersonic shock compression ramps
US7293955B2 (en) * 2002-09-26 2007-11-13 Ramgen Power Systrms, Inc. Supersonic gas compressor
US20040187475A1 (en) * 2002-11-12 2004-09-30 Usab William J. Apparatus and method for reducing radiated sound produced by a rotating impeller
US7234914B2 (en) * 2002-11-12 2007-06-26 Continum Dynamics, Inc. Apparatus and method for enhancing lift produced by an airfoil
US20060254271A1 (en) * 2005-05-13 2006-11-16 Ishikawajima-Harima Heavy Industries Co., Ltd. Apparatus for controlling microwave reflecting
US7861823B2 (en) * 2005-11-04 2011-01-04 United Technologies Corporation Duct for reducing shock related noise
US20090317237A1 (en) * 2008-06-20 2009-12-24 General Electric Company System and method for reduction of unsteady pressures in turbomachinery
WO2014143267A1 (en) 2013-03-15 2014-09-18 United Technologies Corporation Gas turbine engine with low fan noise
GB2516648B (en) * 2013-07-29 2016-08-31 Charles Wells John Fitting for a gas turbine engine
US10378554B2 (en) * 2014-09-23 2019-08-13 Pratt & Whitney Canada Corp. Gas turbine engine with partial inlet vane
US20180156236A1 (en) * 2016-12-02 2018-06-07 Pratt & Whitney Canada Corp. Gas turbine engine bleed configuration
US10563513B2 (en) 2017-12-19 2020-02-18 United Technologies Corporation Variable inlet guide vane
CN109159902B (en) * 2018-08-23 2020-08-21 金湖县农副产品营销协会 Drainage mechanism for air inlet of unmanned aerial vehicle engine

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2623688A (en) * 1945-12-13 1952-12-30 Power Jets Res & Dev Ltd Rotary power conversion machine
US3574477A (en) * 1969-02-19 1971-04-13 Boeing Co Noise attenuating system for rotary engines
FR2083742A5 (en) * 1970-03-23 1971-12-17 Cit Alcatel
US3820918A (en) * 1972-01-21 1974-06-28 N A S A Supersonic fan blading
US3829237A (en) * 1972-06-27 1974-08-13 Nasa Variably positioned guide vanes for aerodynamic choking

Also Published As

Publication number Publication date
FR2256315B3 (en) 1977-08-12
FR2256315A1 (en) 1975-07-25
CA1000207A (en) 1976-11-23
US3873229A (en) 1975-03-25

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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