GB1310910A – Sound control of tubofan engines
– Google Patents
GB1310910A – Sound control of tubofan engines
– Google Patents
Sound control of tubofan engines
Info
Publication number
GB1310910A
GB1310910A
GB1737670A
GB1737670A
GB1310910A
GB 1310910 A
GB1310910 A
GB 1310910A
GB 1737670 A
GB1737670 A
GB 1737670A
GB 1737670 A
GB1737670 A
GB 1737670A
GB 1310910 A
GB1310910 A
GB 1310910A
Authority
GB
United Kingdom
Prior art keywords
nozzle
fan
air
gaseous
stream
Prior art date
1969-04-18
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
GB1737670A
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.)
General Electric Co
Original Assignee
General Electric Co
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.)
1969-04-18
Filing date
1970-04-13
Publication date
1973-03-21
1970-04-13
Application filed by General Electric Co
filed
Critical
General Electric Co
1973-03-21
Publication of GB1310910A
publication
Critical
patent/GB1310910A/en
Status
Expired
legal-status
Critical
Current
Links
Espacenet
Global Dossier
Discuss
Classifications
F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
F02K—JET-PROPULSION PLANTS
F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
F02K3/08—Plants including a gas turbine driving a compressor or a ducted fan with supplementary heating of the working fluid; Control thereof
F02K3/105—Heating the by-pass flow
F02K3/11—Heating the by-pass flow by means of burners or combustion chambers
F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
F02K—JET-PROPULSION PLANTS
F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
F02K1/28—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto using fluid jets to influence the jet flow
F02K1/34—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto using fluid jets to influence the jet flow for attenuating noise
F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
F02K—JET-PROPULSION PLANTS
F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
F02K1/38—Introducing air inside the jet
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
1310910 Gas turbine ducted fan engines GENERAL ELECTRIC CO 13 April 1970 [18 April 1969] 17376/70 Heading F1J A gas turbine ducted fan engine comprises a propulsive nozzle from which the air stream is discharged to provide propulsive thrust there being means for generating a gas stream in which the speed of propagation of sound energy is substantially higher than it is in the fan air stream and means for discharging the gas stream adjacent or from at least the lower portions of the nozzle so as to form a gaseous shroud for the air stream whereby sound energy within the air stream is limited as to its angle of propagation from the nozzle. The engine shown in Fig. 2, comprises a ducted fan having blades 12, part of the air from the fan passing to the core engine and part passing through the passage 26 defined between the inner and outer casings 18, 16 and discharging through the annular nozzle 28. The outer casing 16 is shaped to define an annular discharge nozzle 30 through which a stream of gaseous fluid from a generator indicated at 32 is discharged in the form of an annular gaseous shroud around the air stream discharging from the propulsion nozzle 28. The angle of noise level propagation is thus limited as shown so that less noise passes to a point beneath the engine. In Fig. 4 the outer fan casing 44 is short and the gaseous shroud is formed by combustion gases generated in a chamber 58 and discharged through annular nozzle 56. Part of the air from the fan duct passes through opening 52 to the combustion chamber 58. In a further embodiment water is passed through a coil disposed around the combustion equipment of the core engine and the steam generated therein is discharged through a nozzle 56 so as to form a gaseous shroud around the fan air discharge. The gaseous shroud may be formed only at the lower side of the fan air discharge.
GB1737670A
1969-04-18
1970-04-13
Sound control of tubofan engines
Expired
GB1310910A
(en)
Applications Claiming Priority (1)
Application Number
Priority Date
Filing Date
Title
US81743269A
1969-04-18
1969-04-18
Publications (1)
Publication Number
Publication Date
GB1310910A
true
GB1310910A
(en)
1973-03-21
Family
ID=25223075
Family Applications (1)
Application Number
Title
Priority Date
Filing Date
GB1737670A
Expired
GB1310910A
(en)
1969-04-18
1970-04-13
Sound control of tubofan engines
Country Status (5)
Country
Link
US
(1)
US3527317A
(en)
BE
(1)
BE748387A
(en)
DE
(1)
DE2017772A1
(en)
FR
(1)
FR2045363A5
(en)
GB
(1)
GB1310910A
(en)
Cited By (2)
* Cited by examiner, † Cited by third party
Publication number
Priority date
Publication date
Assignee
Title
GB2249140A
(en)
*
1990-08-30
1992-04-29
S & C Thermofluids Ltd
Noise suppression in gas turbine engine
CN103520939A
(en)
*
2013-10-25
2014-01-22
江南大学
Voice-control automatic gear shifting fan toy
Families Citing this family (29)
* Cited by examiner, † Cited by third party
Publication number
Priority date
Publication date
Assignee
Title
US3655009A
(en)
*
1969-09-18
1972-04-11
Rohr Corp
Method and apparatus for suppressing the noise of a fan-jet engine
US3578106A
(en)
*
1969-10-15
1971-05-11
Rohr Corp
Turbofan propulsion silencing apparatus
US3726091A
(en)
*
1971-02-16
1973-04-10
Rohr Corp
Sound suppressing apparatus
US3815356A
(en)
*
1971-03-10
1974-06-11
Trw Inc
Foam cooling and acoustic damping of exhaust gases produced by an internal combustion engine
BE791058A
(en)
*
1971-11-08
1973-03-01
Boeing Co
INCREASED OR VARIABLE DERIVATION RATE ENGINES
US3991849A
(en)
*
1974-06-19
1976-11-16
United Technologies Corporation
Sound absorption with variable acoustic resistance means
GB1553012A
(en)
*
1976-05-13
1979-09-19
United Technologies Corp
Method for reducing the noise level in a turbofan engine and turbofan engine
US4135363A
(en)
*
1976-05-13
1979-01-23
United Technologies Corporation
Device to provide flow inversion in a turbofan exhaust tailpipe to achieve low jet noise
US4288984A
(en)
*
1978-09-19
1981-09-15
The Boeing Company
Noise suppressing turbofan nozzles and method
US4306412A
(en)
*
1978-11-24
1981-12-22
The Boeing Company
Jet engine and method of operating the same
US4280587A
(en)
*
1979-05-08
1981-07-28
The Boeing Company
Noise-suppressing jet engine nozzles and method
US4291782A
(en)
*
1979-10-30
1981-09-29
The Boeing Company
Simplified method and apparatus for hot-shield jet noise suppression
FR2589713A1
(en)
*
1985-11-08
1987-05-15
Gradient
APPARATUS FOR DETECTING CARDIO-RESPIRATORY INSUFFICIENCY
US5092425A
(en)
*
1990-04-02
1992-03-03
The United States Of America As Represented By The Secretary Of The Air Force
Jet noise suppressor and method
AU2002211367A1
(en)
*
2000-10-02
2002-04-15
Rohr, Inc.
Apparatus, method and system for gas turbine engine noise reduction
US7581692B2
(en)
*
2003-06-30
2009-09-01
General Electric Company
Fluidic chevrons and configurable thermal shield for jet noise reduction
US7624666B1
(en)
*
2003-07-08
2009-12-01
Raytheon Company
Obscuration method for reducing the infrared signature of an object
US20050138932A1
(en)
*
2003-10-22
2005-06-30
Perricone Nicholas V.
Aircraft protection method and system
US20050091963A1
(en)
*
2003-10-30
2005-05-05
Gongling Li
Aircraft turbine engine and an air ejection assembly for use therewith
US7308966B2
(en)
*
2003-12-30
2007-12-18
General Electric Company
Device for reducing jet engine exhaust noise using oscillating jets
US7412832B2
(en)
*
2004-03-26
2008-08-19
General Electric Company
Method and apparatus for operating gas turbine engines
US7246481B2
(en)
*
2004-03-26
2007-07-24
General Electric Company
Methods and apparatus for operating gas turbine engines
EP2061964B1
(en)
*
2006-10-12
2015-03-04
United Technologies Corporation
Turbofan engine having inner fixed structure including ducted passages
DE102009032841A1
(en)
*
2009-07-13
2011-01-20
Rolls-Royce Deutschland Ltd & Co Kg
Noise-reduced aircraft engine and method for reducing noise emissions of an aircraft engine
US20110162339A1
(en)
*
2011-01-07
2011-07-07
Braden Manufacturing, Llc
Flow distribution of gas turbine exhaust using walls shaped to facilitate improved gas flow
US8375699B1
(en)
*
2012-01-31
2013-02-19
United Technologies Corporation
Variable area fan nozzle with wall thickness distribution
US10415468B2
(en)
2012-01-31
2019-09-17
United Technologies Corporation
Gas turbine engine buffer system
US9394852B2
(en)
2012-01-31
2016-07-19
United Technologies Corporation
Variable area fan nozzle with wall thickness distribution
US10040560B2
(en)
*
2015-09-30
2018-08-07
The Boeing Company
Trailing edge core compartment vent for an aircraft engine
Family Cites Families (4)
* Cited by examiner, † Cited by third party
Publication number
Priority date
Publication date
Assignee
Title
US2931169A
(en)
*
1956-05-15
1960-04-05
Westinghouse Electric Corp
Variable convergent-divergent exhaust nozzle
FR1157063A
(en)
*
1956-07-30
1958-05-27
Bertin & Cie
Mufflers for engines, in particular for jet engines
US3069848A
(en)
*
1959-02-23
1962-12-25
Rolls Royce
Jet lift gas turbine engines having thrust augmenting and silencing means
US3187501A
(en)
*
1960-12-19
1965-06-08
Thomas E Quick
Method of and apparatus for augmenting thrust and suppressing sound in aircraft, rockets, and the like
1969
1969-04-18
US
US817432A
patent/US3527317A/en
not_active
Expired – Lifetime
1970
1970-04-02
BE
BE748387D
patent/BE748387A/en
unknown
1970-04-13
GB
GB1737670A
patent/GB1310910A/en
not_active
Expired
1970-04-14
DE
DE19702017772
patent/DE2017772A1/en
active
Pending
1970-04-16
FR
FR7013846A
patent/FR2045363A5/fr
not_active
Expired
Cited By (3)
* Cited by examiner, † Cited by third party
Publication number
Priority date
Publication date
Assignee
Title
GB2249140A
(en)
*
1990-08-30
1992-04-29
S & C Thermofluids Ltd
Noise suppression in gas turbine engine
GB2249140B
(en)
*
1990-08-30
1994-12-07
S & C Thermofluids Ltd
Aircraft engine noise suppression
CN103520939A
(en)
*
2013-10-25
2014-01-22
江南大学
Voice-control automatic gear shifting fan toy
Also Published As
Publication number
Publication date
US3527317A
(en)
1970-09-08
FR2045363A5
(en)
1971-02-26
DE2017772A1
(en)
1970-11-19
BE748387A
(en)
1970-09-16
Similar Documents
Publication
Publication Date
Title
GB1310910A
(en)
1973-03-21
Sound control of tubofan engines
US4122674A
(en)
1978-10-31
Apparatus for suppressing combustion noise within gas turbine engines
US4156344A
(en)
1979-05-29
Inlet guide vane bleed system
US3830431A
(en)
1974-08-20
Abating exhaust noises in jet engines
US5092425A
(en)
1992-03-03
Jet noise suppressor and method
GB1464971A
(en)
1977-02-16
Gas turbine engines including sound attenuating air inlet ducts
GB1122684A
(en)
1968-08-07
Improvements in axial flow separator for a gas turbine engine
GB1121960A
(en)
1968-07-31
Improvements relating to jet propulsion engines
GB1052328A
(en)
1966-12-21
Improvements in or relating to gas turbine engine combustion equipment
GB749009A
(en)
1956-05-16
An improved jet propulsion plant
GB1128431A
(en)
1968-09-25
Internal combustion engine turbocharger
GB1055625A
(en)
1967-01-18
Improved vehicle for launching rocket propelled vehicles
US3693749A
(en)
1972-09-26
Reduction of gas turbine engine noise annoyance by modulation
GB1413845A
(en)
1975-11-12
Marine propulsion
GB1122910A
(en)
1968-08-07
Improvements in supersonic convergent-divergent jet exhaust nozzle
GB1110154A
(en)
1968-04-18
Aircraft jet power plant
GB1270434A
(en)
1972-04-12
Turbofan engines
GB744196A
(en)
1956-02-01
Improvements in or relating to silencing means
GB1307867A
(en)
1973-02-21
Device for attenuating noise emitted by the jet of a jet engine
GB1535765A
(en)
1978-12-13
Variable cycle turbofan engines
GB627634A
(en)
1949-08-12
Improvements in or relating to gas turbine aircraft propulsion power plants
GB1468726A
(en)
1977-03-30
Gas turbine engines
US3533237A
(en)
1970-10-13
Low drag nacelle arrangement for jet propulsion power plants
FR2389772A1
(en)
1978-12-01
Jet engine for subsonic aircraft – has hollow rotor with internal blades to produce secondary stream of air within annular primary stream
GB1055380A
(en)
1967-01-18
Gas turbine engine
Legal Events
Date
Code
Title
Description
1973-08-01
PS
Patent sealed
1975-11-05
PLNP
Patent lapsed through nonpayment of renewal fees
