GB838617A - Improved jet noise suppressor nozzle - Google Patents

Improved jet noise suppressor nozzle

Info

Publication number
GB838617A
GB838617A GB27685/57A GB2768557A GB838617A GB 838617 A GB838617 A GB 838617A GB 27685/57 A GB27685/57 A GB 27685/57A GB 2768557 A GB2768557 A GB 2768557A GB 838617 A GB838617 A GB 838617A
Authority
GB
United Kingdom
Prior art keywords
nozzle
lobes
radial
lobe
skin
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
GB27685/57A
Inventor
David Morris Brown
John Michael Storer Keen
Bertram Harry Urmston
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB27685/57A priority Critical patent/GB838617A/en
Priority to US756659A priority patent/US3092205A/en
Priority to CH6326458A priority patent/CH366174A/en
Priority to FR1201893D priority patent/FR1201893A/en
Priority to DER23966A priority patent/DE1100384B/en
Publication of GB838617A publication Critical patent/GB838617A/en
Expired legal-status Critical Current

Links

Classifications

    • 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
    • F02K1/48—Corrugated nozzles
    • 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
    • F02K1/40—Nozzles having means for dividing the jet into a plurality of partial jets or having an elongated cross-section outlet

Abstract

838,617. Jet-propulsion nozzles. ROLLSROYCE Ltd. Aug. 12, 1958 [Sept. 2, 1957], No. 27685/57. Class 110 (3). A jet noise suppressor nozzle comprises a plurality of longitudinally extending, substantially radial hollow lobes through which the hot jet gases flow, the lobes being angularly spaced from each other in a circular arrangement and increasing in radial extent in the downstream direction and having substantially radially extending walls which are corrugated at least in part substantially longitudinally. The nozzle 10, Fig. 1, comprises a plurality of longitudinally extending substantially radial, hollow lobes 8 through which the hot gases flow in the direction of the arrow 9. Each lobe 8 increases in radial extent in a downstream direction and increases in cross-sectional width radially outwards. The radial walls 8<1>, 8<11> are formed from an internal skin 12, Fig. 3, which forms the gas passage and an external skin 11. The two radial walls of the skin 12 are corrugated symmetrically at 14. The corrugations which extend longitudinally of the nozzle but do reach its downstream edge, form in transverse section, a bubbular configuration. The hoop stress in each bubble is taken by longitudinal stiffeners 16 joined by discrete transverse local ties or struts 13 of aerofoil section. The skins 11 and 12 are braced by struts 15 attached to the stiffeners 16. Additional longitudinal stiffeners may be attached to the internal skin of each lobe 8. In a modification, Fig. 6 (not shown), a lobulated frame is located internally of the downstream end of the nozzle, the lobes of which are attached to the lobes 8 to brace them. In this arrangement, the members 13 are replaced by continuous I- shaped members. Each lobe 8 may have a throat to form a convergent - divergent nozzle.
GB27685/57A 1957-09-02 1957-09-02 Improved jet noise suppressor nozzle Expired GB838617A (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
GB27685/57A GB838617A (en) 1957-09-02 1957-09-02 Improved jet noise suppressor nozzle
US756659A US3092205A (en) 1957-09-02 1958-08-22 Jet noise suppressor nozzle
CH6326458A CH366174A (en) 1957-09-02 1958-08-25 Nozzle to suppress the noise of jet engines
FR1201893D FR1201893A (en) 1957-09-02 1958-08-28 Jet engine nozzle designed to suppress noise
DER23966A DE1100384B (en) 1957-09-02 1958-08-30 Duese for suppressing the noise in jet engines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB27685/57A GB838617A (en) 1957-09-02 1957-09-02 Improved jet noise suppressor nozzle

Publications (1)

Publication Number Publication Date
GB838617A true GB838617A (en) 1960-06-22

Family

ID=10263626

Family Applications (1)

Application Number Title Priority Date Filing Date
GB27685/57A Expired GB838617A (en) 1957-09-02 1957-09-02 Improved jet noise suppressor nozzle

Country Status (5)

Country Link
US (1) US3092205A (en)
CH (1) CH366174A (en)
DE (1) DE1100384B (en)
FR (1) FR1201893A (en)
GB (1) GB838617A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3572464A (en) * 1969-10-06 1971-03-30 Rohr Corp Method and apparatus for suppressing the noise of a fan-jet engine

Families Citing this family (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1229337B (en) * 1960-10-31 1966-11-24 Bristol Siddeley Engines Ltd Curved gas outlet nozzle
US3415337A (en) * 1966-04-20 1968-12-10 Gen Electric Air injector device for air-cooled noise suppressors
GB1127826A (en) * 1966-06-17 1968-09-18 Rolls Royce Gas turbine engine
US3647021A (en) * 1970-06-22 1972-03-07 Rohr Corp Sound suppression system
US4165609A (en) * 1977-03-02 1979-08-28 The Boeing Company Gas turbine mixer apparatus
US4215536A (en) * 1978-12-26 1980-08-05 The Boeing Company Gas turbine mixer apparatus
US4302934A (en) * 1979-11-01 1981-12-01 United Technologies Corporation Lobed mixer/inverter
US4335801A (en) * 1980-12-15 1982-06-22 The Boeing Company Noise suppressing nozzle
US4474259A (en) * 1982-04-26 1984-10-02 The Boeing Company Internally ventilated noise suppressor for jet engine
US6098402A (en) * 1989-02-10 2000-08-08 Sawruk; Stephen D. Infra-red stealth masking device (IRSMD)
US5265807A (en) * 1992-06-01 1993-11-30 Rohr, Inc. Aerodynamic stiffening ring for an aircraft turbine engine mixer
EP0635632B1 (en) * 1993-06-25 1997-10-22 THE NORDAM GROUP, Inc. Noise suppression system
JP4724986B2 (en) * 2001-08-29 2011-07-13 株式会社Ｉｈｉ Lobe mixer
DE60329905D1 (en) * 2002-02-22 2009-12-17 Nordam Group Inc DOUBLE MIXER exhaust nozzle
US7963099B2 (en) * 2007-05-21 2011-06-21 General Electric Company Fluted chevron exhaust nozzle
US7882696B2 (en) * 2007-06-28 2011-02-08 Honeywell International Inc. Integrated support and mixer for turbo machinery
US8087250B2 (en) * 2008-06-26 2012-01-03 General Electric Company Duplex tab exhaust nozzle
US8734085B2 (en) 2009-08-17 2014-05-27 Pratt & Whitney Canada Corp. Turbine section architecture for gas turbine engine
US9759159B2 (en) 2014-05-26 2017-09-12 Pratt & Whitney Canada Corp. Integrated turbine exhaust struts and mixer of turbofan engine
US10018150B2 (en) 2014-05-26 2018-07-10 Pratt & Whitney Canada Inc. Integrated TEC/mixer strut axial position
US9745919B2 (en) * 2014-07-30 2017-08-29 Pratt & Whitney Canada Corp. Gas turbine engine exhaust ejector/mixer
US10197009B2 (en) * 2014-07-30 2019-02-05 Pratt & Whitney Canada Corp. Gas turbine engine ejector
FR3036139B1 (en) * 2015-05-12 2019-12-13 Safran Aircraft Engines TURBOMACHINE COMPRISING A LOBE MIXER WITH SCOOPERS.
US11028778B2 (en) 2018-09-27 2021-06-08 Pratt & Whitney Canada Corp. Engine with start assist
US11448160B2 (en) * 2019-09-23 2022-09-20 General Electric Company High temperature gradient gas mixer
CN111997780A (en) * 2020-09-02 2020-11-27 南昌航空大学 Claw-type wave crest spoiler for alternating lobe spray pipe

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2029337A (en) * 1932-11-21 1936-02-04 California Spray Chemical Corp Nozzle
GB428257A (en) * 1934-05-14 1935-05-09 Einar Olof Eugen Tyden Silencer for internal combustion engines
US2396208A (en) * 1943-03-08 1946-03-05 Anemostat Corp Method of and means for treating gases
US2484826A (en) * 1945-02-02 1949-10-18 Bertron G Harley Silencer with flattened corrugated gas passage
GB685939A (en) * 1950-05-17 1953-01-14 Rolls Royce Improvements in or relating to gas-turbine engine structures
GB766986A (en) * 1952-07-25 1957-01-30 Geoffrey Michael Lilley Noise suppressing nozzles for aircraft jet propulsion engines
NL98695C (en) * 1952-07-25
BE521636A (en) * 1952-07-25
GB744196A (en) * 1953-08-12 1956-02-01 Rolls Royce Improvements in or relating to silencing means
US2931169A (en) * 1956-05-15 1960-04-05 Westinghouse Electric Corp Variable convergent-divergent exhaust nozzle

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3572464A (en) * 1969-10-06 1971-03-30 Rohr Corp Method and apparatus for suppressing the noise of a fan-jet engine

Also Published As

Publication number Publication date
US3092205A (en) 1963-06-04
CH366174A (en) 1962-12-15
FR1201893A (en) 1960-01-06
DE1100384B (en) 1961-02-23

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