GB1207194A - Jet engines having means for reducing the noise level - Google Patents
Jet engines having means for reducing the noise levelInfo
- Publication number
- GB1207194A GB1207194A GB56151/67A GB5615167A GB1207194A GB 1207194 A GB1207194 A GB 1207194A GB 56151/67 A GB56151/67 A GB 56151/67A GB 5615167 A GB5615167 A GB 5615167A GB 1207194 A GB1207194 A GB 1207194A
- Authority
- GB
- United Kingdom
- Prior art keywords
- doors
- pod
- annular
- nacelle
- duct
- 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
Links
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N27/00—Investigating or analysing materials by the use of electric, electrochemical, or magnetic means
- G01N27/26—Investigating or analysing materials by the use of electric, electrochemical, or magnetic means by investigating electrochemical variables; by using electrolysis or electrophoresis
- G01N27/403—Cells and electrode assemblies
- G01N27/404—Cells with anode, cathode and cell electrolyte on the same side of a permeable membrane which separates them from the sample fluid, e.g. Clark-type oxygen sensors
-
- 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
- F02K1/06—Varying effective area of jet pipe or nozzle
- F02K1/12—Varying effective area of jet pipe or nozzle by means of pivoted flaps
- F02K1/123—Varying effective area of jet pipe or nozzle by means of pivoted flaps of two series of flaps, both having their flaps hinged at their upstream ends on a fixed structure
-
- 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
- F02K1/46—Nozzles having means for adding air to the jet or for augmenting the mixing region between the jet and the ambient air, e.g. for silencing
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N7/00—Analysing materials by measuring the pressure or volume of a gas or vapour
- G01N7/10—Analysing materials by measuring the pressure or volume of a gas or vapour by allowing diffusion of components through a porous wall and measuring a pressure or volume difference
Abstract
1,207,194. Jet propulsion nozzles. UNITED AIRCRAFT CORP. Dec.11, 1967 [Dec.28, 1966], No.56151/67. Heading F1J. A jet engine arranged for the suppression of jet sound comprises a pod or nacelle surrounding a duct for exhaust gas flow, flaps positioned to form a converging section adjacent the end of the duct, blow-in doors pivotally mounted at the end of the pod or nacelle to move inwardly, an annular body positioned rearwardly of the pod or nacelle with the inner surface of the body forming an inlet passageway with each blow-in door, and turbulenceinducing means to produce a shear layer surrounding the expanding exhaust flow. An engine having a primary flow between a wall 20, Fig.8, and a centre core 22 and a by-pass flow through an annular duct 6 extending rearwardly of a fan and bounded by walls 8, 13, comprises a circumferential series of pivoted doors 37 extending rearwardly from a pod or nacelle 35, pivoted flaps 41 extending rearwardly from an annular shroud 39, and the two clamshells 43 of a clamshell nozzle mounted within the shroud 39. The members 37, 41, 43 occupy the dotted position during supersonic flight and the full-line positions during subsonic flight. Flaps 33 are slidably mounted on a track mechanism 30 to provide a nozzle of variable convergency. The rear ends of the walls 13, 20 are connected by a flat annular base 28 which promotes a turbulent layer between the primary and by-pass flows, the turbulence being increased by directing gas through slots or holes 51a from an annular manifold 58 fed via a conduit 55 with gas under pressure, e.g. air from the engine compressor. A further turbulent region downstream of the doors 37 is induced by gas discharged from an annular manifold 57 through openings 59. The turbulent regions reduce noise during take-off. Each door 37 comprises a front section 37a pivoted to the pod or nacelle 35 and a rear section 37b hinged to the front section at 54, a roller 56 at the hinge travelling in a cam opening which is part of a linkage connecting the doors 37 and the clamshells 43. The clamshells may, however, be arranged to be movable independently of the doors 37. The engine may be of non-bypass form, with doors 44, Fig.3, extending rearwardly from a pod or nozzle around a jet duct 26 terminating in a nozzle formed by fixed or movable flaps 10. The doors 44 are shown in the inward position. Gas for promoting turbulence downstream of the doors 44 is discharged through a long narrow slot 66 or a line of holes formed in each of a number of manifold sections 62. The rear end of the duct 26 is of polygonal form with each side of the polygon having a mounting sleeve 60 containing one of the manifold sections 62. The manifold sections 62 can be pivoted in unison by the linkage shown to adjust the direction of discharge from the slot 66. In other constructions, the direction of discharge is fixed. The outside surface of the door 44 may be roughened to promote turbulence. The doors 44 and pivoted flaps (46), Fig .1 (not shown) extending rearwardly from an annular shroud (40) may be either power-actuated or freely floating.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US60545466A | 1966-12-28 | 1966-12-28 | |
GB828/67A GB1215446A (en) | 1966-12-28 | 1967-01-06 | Apparatus for measuring or detecting dissolved oxygen and process employing said apparatus |
Publications (1)
Publication Number | Publication Date |
---|---|
GB1207194A true GB1207194A (en) | 1970-09-30 |
Family
ID=26236212
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB828/67A Expired GB1215446A (en) | 1966-12-28 | 1967-01-06 | Apparatus for measuring or detecting dissolved oxygen and process employing said apparatus |
GB56151/67A Expired GB1207194A (en) | 1966-12-28 | 1967-12-11 | Jet engines having means for reducing the noise level |
Family Applications Before (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB828/67A Expired GB1215446A (en) | 1966-12-28 | 1967-01-06 | Apparatus for measuring or detecting dissolved oxygen and process employing said apparatus |
Country Status (5)
Country | Link |
---|---|
US (1) | US3463402A (en) |
BE (1) | BE709007A (en) |
DE (1) | DE1626148B1 (en) |
FR (2) | FR1553178A (en) |
GB (2) | GB1215446A (en) |
Cited By (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS5025920A (en) * | 1973-03-19 | 1975-03-18 | ||
GB2119023A (en) * | 1982-04-15 | 1983-11-09 | Secr Defence | Jet propulsion nozzle having a shroud |
GB2207708A (en) * | 1987-07-24 | 1989-02-08 | Thomas Edward Friedrich | Arrangement for supressing jet engine noise |
GB2244098A (en) * | 1990-05-17 | 1991-11-20 | Secr Defence | Variable configuration gas turbine engine |
GB2249140A (en) * | 1990-08-30 | 1992-04-29 | S & C Thermofluids Ltd | Noise suppression in gas turbine engine |
FR2919662A1 (en) * | 2007-08-02 | 2009-02-06 | Eads Deutschland Gmbh | TUBE DEVICE FOR A GAS TURBINE ENGINE |
US10371094B2 (en) | 2014-07-09 | 2019-08-06 | Rolls-Royce Plc | Nozzle arrangement for a gas turbine engine |
US10549863B2 (en) | 2014-08-20 | 2020-02-04 | Bombardier Inc. | Actuated outlet door for aircraft high-temperature exhaust |
Families Citing this family (41)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3635308A (en) * | 1969-07-03 | 1972-01-18 | Rohr Corp | Sound suppression system |
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 |
US3575261A (en) * | 1969-10-24 | 1971-04-20 | Rohr Corp | Fan jet silencer with fluid mixture |
US3667680A (en) * | 1970-04-24 | 1972-06-06 | Boeing Co | Jet engine exhaust nozzle system |
US3648800A (en) * | 1970-04-27 | 1972-03-14 | Gen Electric | Coanda expansion exhaust nozzle suppressor |
US3726091A (en) * | 1971-02-16 | 1973-04-10 | Rohr Corp | Sound suppressing apparatus |
US3711013A (en) * | 1971-04-26 | 1973-01-16 | Rohr Corp | Thrust control and sound apparatus |
GB1395709A (en) * | 1971-07-06 | 1975-05-29 | Rolls Royce | Jet propulsion power plant |
US3739984A (en) * | 1971-08-25 | 1973-06-19 | Rohr Industries Inc | Thrust augmenting and south suppressing apparatus and method |
FR2166296B1 (en) * | 1972-01-06 | 1974-10-18 | Onera (Off Nat Aerospatiale) | |
US3826331A (en) * | 1972-02-29 | 1974-07-30 | Bolt Beranek & Newman | Method of and apparatus for reducing sound generated by surfaces in fluid jet streams and the like |
GB1436796A (en) * | 1972-08-22 | 1976-05-26 | Mtu Muenchen Gmbh | Gas turbine ducted fan engines of multi-shaft and multi-flow construction |
JPS51131099A (en) * | 1975-05-06 | 1976-11-15 | Toshio Horiuchi | Silencer making use of the turbulence of fluid |
US3982696A (en) * | 1975-07-01 | 1976-09-28 | Grumman American Aviation Corporation | Jet noise suppressor nozzle |
US4372110A (en) * | 1976-02-13 | 1983-02-08 | Nasa | Noise suppressor for turbo fan jet engines |
US4269685A (en) * | 1979-10-16 | 1981-05-26 | Mcneilabs, Inc. | Disposable polarographic gas sensor system |
US4284170A (en) * | 1979-10-22 | 1981-08-18 | United Technologies Corporation | Gas turbine noise suppressor |
US4291782A (en) * | 1979-10-30 | 1981-09-29 | The Boeing Company | Simplified method and apparatus for hot-shield jet noise suppression |
US5038559A (en) * | 1981-12-22 | 1991-08-13 | Allied-Signal Inc. | Method and apparatus for selectively varying an effective fluid flow area of a jet engine exhaust nozzle |
GB8622502D0 (en) * | 1986-09-18 | 1986-10-22 | Bass Plc | Brewing beer |
DE8915860U1 (en) * | 1989-02-08 | 1991-12-05 | Mtu Muenchen Gmbh | |
US5162620A (en) * | 1989-11-28 | 1992-11-10 | Allied-Signal Inc. | Dual flow turbine engine muffler |
US5435127A (en) * | 1993-11-15 | 1995-07-25 | General Electric Company | Method and apparatus for boosting ram airflow to an ejection nozzle |
US5428954A (en) * | 1994-04-11 | 1995-07-04 | Cowan, Sr.; Howard H. | System for suppressing engine exhaust noise |
US5884472A (en) * | 1995-10-11 | 1999-03-23 | Stage Iii Technologies, L.C. | Alternating lobed mixer/ejector concept suppressor |
US5761900A (en) * | 1995-10-11 | 1998-06-09 | Stage Iii Technologies, L.C. | Two-stage mixer ejector suppressor |
US5799874A (en) * | 1995-11-30 | 1998-09-01 | United Technologies Corporation | Aerodynamically controlled ejector |
DE19642393A1 (en) * | 1996-10-14 | 1998-04-16 | Mtu Muenchen Gmbh | Turbo jet engine with a flower mixer |
US5884843A (en) * | 1996-11-04 | 1999-03-23 | The Boeing Company | Engine noise suppression ejector nozzle |
US5941065A (en) * | 1996-11-04 | 1999-08-24 | The Boeing Company | Stowable mixer ejection nozzle |
US5908159A (en) * | 1997-02-24 | 1999-06-01 | The Boeing Company | Aircraft chute ejector nozzle |
US5826794A (en) * | 1997-02-28 | 1998-10-27 | The Boeing Company | Aircraft scoop ejector nozzle |
US6012281A (en) * | 1997-08-18 | 2000-01-11 | United Technologies Corporation | Noise suppressing fluid mixing system for a turbine engine |
US7293401B2 (en) * | 2002-03-20 | 2007-11-13 | The Regents Of The University Of California | Jet engine noise suppressor |
US8225592B1 (en) * | 2003-06-09 | 2012-07-24 | Florida State University Research Foundation | Microjet noise suppression system for jet engines |
US7412832B2 (en) * | 2004-03-26 | 2008-08-19 | General Electric Company | Method and apparatus for operating gas turbine engines |
FR2896274B1 (en) * | 2006-01-13 | 2008-04-18 | Snecma Sa | VARIABLE SECTION FLOW MIXER FOR DOUBLE TURBOREACTOR FLOW OF SUPERSONIC AIRPLANE |
US8192158B1 (en) | 2008-12-12 | 2012-06-05 | Mainstream Engineering Corp. | Apparatus and method to increase total-to-static pressure ratio across a turbine |
US8480361B1 (en) | 2010-01-26 | 2013-07-09 | Mainstream Engineering Corporation | Enhanced system and method to increase the total-to-static pressure ratio across a RAM air turbine using surface contoured flow agitators |
US8794902B1 (en) | 2010-01-26 | 2014-08-05 | II Daniel K. Van Ness | System and method to improve the exhaust pressure across a RAM air turbine through secondary flow mixing |
Family Cites Families (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2747367A (en) * | 1950-03-21 | 1956-05-29 | United Aircraft Corp | Gas turbine power plant supporting structure |
US2815643A (en) * | 1951-06-29 | 1957-12-10 | United Aircraft Corp | Variable area nozzle |
US2836034A (en) * | 1951-06-29 | 1958-05-27 | United Aircraft Corp | Variable area nozzle |
US2934889A (en) * | 1956-02-14 | 1960-05-03 | United Aircraft Corp | Noise abatement means |
FR1157063A (en) * | 1956-07-30 | 1958-05-27 | Bertin & Cie | Mufflers for engines, in particular for jet engines |
US2955418A (en) * | 1958-08-06 | 1960-10-11 | Ryan Aeronautical Co | Combination augmenter, sound suppressor and thrust reverser for jet engines |
US3062003A (en) * | 1959-04-06 | 1962-11-06 | United Aircraft Corp | Variable area exhaust nozzle |
US3057150A (en) * | 1961-03-27 | 1962-10-09 | United Aircraft Corp | Two dimensional floating blow-in-door and flap ejector |
US3215172A (en) * | 1962-12-24 | 1965-11-02 | Nilsson Robbins & Anderson | Jet engine noise suppressor with shroud for aspiration of air into exhaust stream |
US3227240A (en) * | 1964-05-04 | 1966-01-04 | Gen Electric | Air mingling sound suppressor for jet engine |
-
1966
- 1966-12-28 US US605454A patent/US3463402A/en not_active Expired - Lifetime
-
1967
- 1967-01-06 GB GB828/67A patent/GB1215446A/en not_active Expired
- 1967-12-11 GB GB56151/67A patent/GB1207194A/en not_active Expired
- 1967-12-23 DE DE1967U0014536 patent/DE1626148B1/en active Pending
- 1967-12-26 FR FR1553178D patent/FR1553178A/fr not_active Expired
- 1967-12-28 FR FR1553172D patent/FR1553172A/fr not_active Expired
-
1968
- 1968-01-05 BE BE709007D patent/BE709007A/xx unknown
Cited By (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS5025920A (en) * | 1973-03-19 | 1975-03-18 | ||
JPS5922062B2 (en) * | 1973-03-19 | 1984-05-24 | ゼネラル エレクトリツク カンパニイ | turbofan engine |
GB2119023A (en) * | 1982-04-15 | 1983-11-09 | Secr Defence | Jet propulsion nozzle having a shroud |
GB2207708B (en) * | 1987-07-24 | 1991-11-20 | Thomas Edward Friedrich | Arrangement for supressing jet engine noise |
US4934481A (en) * | 1987-07-24 | 1990-06-19 | Friedrich Thomas E | Arrangement for suppressing jet engine noise |
GB2207708A (en) * | 1987-07-24 | 1989-02-08 | Thomas Edward Friedrich | Arrangement for supressing jet engine noise |
GB2244098A (en) * | 1990-05-17 | 1991-11-20 | Secr Defence | Variable configuration gas turbine engine |
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 |
FR2919662A1 (en) * | 2007-08-02 | 2009-02-06 | Eads Deutschland Gmbh | TUBE DEVICE FOR A GAS TURBINE ENGINE |
US9239029B2 (en) | 2007-08-02 | 2016-01-19 | Airbus Defence and Space GmbH | Nozzle arrangement for a gas turbine engine |
US10371094B2 (en) | 2014-07-09 | 2019-08-06 | Rolls-Royce Plc | Nozzle arrangement for a gas turbine engine |
US10549863B2 (en) | 2014-08-20 | 2020-02-04 | Bombardier Inc. | Actuated outlet door for aircraft high-temperature exhaust |
Also Published As
Publication number | Publication date |
---|---|
US3463402A (en) | 1969-08-26 |
FR1553172A (en) | 1969-01-10 |
FR1553178A (en) | 1969-01-10 |
GB1215446A (en) | 1970-12-09 |
BE709007A (en) | 1968-07-05 |
DE1626148B1 (en) | 1971-05-13 |
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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 |