GB1045295A - Improvements in or relating to a jet noise suppression device - Google Patents

Improvements in or relating to a jet noise suppression device

Info

Publication number
GB1045295A
GB1045295A GB1276064A GB1276064A GB1045295A GB 1045295 A GB1045295 A GB 1045295A GB 1276064 A GB1276064 A GB 1276064A GB 1276064 A GB1276064 A GB 1276064A GB 1045295 A GB1045295 A GB 1045295A
Authority
GB
United Kingdom
Prior art keywords
nozzle
vanes
jet
downstream end
shroud
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
GB1276064A
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.)
PETER BRADSHAW
Original Assignee
PETER BRADSHAW
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 PETER BRADSHAW filed Critical PETER BRADSHAW
Priority to GB1276064A priority Critical patent/GB1045295A/en
Publication of GB1045295A publication Critical patent/GB1045295A/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
    • F02K1/38—Introducing air inside the jet
    • F02K1/386—Introducing air inside the jet mixing devices in the jet pipe, e.g. for mixing primary and secondary flow
    • 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
    • F02K1/36—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto having an ejector
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

1,045,295. Jet propulsion nozzles. P. BRADSHAW. June 11, 1965 [March 25, 1964], No. 12760/64. Heading F1J. A noise suppression device for reducing the noise generated by a high velocity gaseous jet issuing into the ambient atmosphere comprises a nozzle having means to impart rotation to the gaseous jet issuing from the nozzle and an ejector shroud disposed about the nozzle. A jet propulsion engine nozzle 10 is provided at its downstream end with a series of vanes 11 which are pivotally mounted about axes 12 normal to the axis of the nozzle whereby the vanes may be moved to a position inclined at angle a to the nozzle axis whereby a rotation is imparted to the jet stream issuing from the nozzle. A shroud ring 10a is disposed around the end of the nozzle 10 and atmospheric air is drawn into the shroud by the jet stream discharging therethrough. The vanes may be fixed in the inclined position. In Fig. 3 not shown the vanes 14 are hollow and atmospheric air is caused to flow therethrough. In Figs. 4 and 5 not shown the downstream end of the nozzle is of corrugated form and a pivotally mounted vane 18 is disposed in the path of the jet stream discharging through each of the corrugations 17. A shroud ring 15a is disposed around the downstream end of the nozzle. Instead of a single vane 18 as in Fig. 4 a pair of vanes 22, 23 Fig. 7 not shown may be associated with each corrugation 17. The invention is applicable also in the case of gas turbine ducted fan engines and gas turbine by-pass engines.
GB1276064A 1964-03-25 1964-03-25 Improvements in or relating to a jet noise suppression device Expired GB1045295A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB1276064A GB1045295A (en) 1964-03-25 1964-03-25 Improvements in or relating to a jet noise suppression device

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1276064A GB1045295A (en) 1964-03-25 1964-03-25 Improvements in or relating to a jet noise suppression device

Publications (1)

Publication Number Publication Date
GB1045295A true GB1045295A (en) 1966-10-12

Family

ID=10010627

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1276064A Expired GB1045295A (en) 1964-03-25 1964-03-25 Improvements in or relating to a jet noise suppression device

Country Status (1)

Country Link
GB (1) GB1045295A (en)

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2467990A1 (en) * 1979-10-22 1981-04-30 United Technologies Corp SILENCER FOR GAS TURBINE
FR2482199A1 (en) * 1980-05-07 1981-11-13 Astech Gas turbine exhaust pipe - has double flow with central pipe having venturi fitted to outer end and included inside final exhaust
GB2119023A (en) * 1982-04-15 1983-11-09 Secr Defence Jet propulsion nozzle having a shroud
US4566270A (en) * 1981-11-03 1986-01-28 Rolls-Royce Limited Gas turbine engine infra-red radiation suppressor
EP1191214A2 (en) * 2000-08-31 2002-03-27 General Electric Company Exhaust nozzle with stub airfoils
EP1870588A1 (en) * 2006-06-19 2007-12-26 Snecma Swirling flow mixing nozzle for a turbomachine
US7735601B1 (en) 2005-03-15 2010-06-15 Rolls-Royce Plc Engine noise
FR2967134A1 (en) * 2010-11-04 2012-05-11 Airbus Operations Sas Nacelle for aircraft jet engine, has nozzle and noise reduction device that is arranged at downstream end of nozzle, where intermediate flow is provided between rest of one flow and rest of another flow in area downstream of device
EP2497934A1 (en) * 2011-03-07 2012-09-12 EADS Construcciones Aeronauticas, S.A. Flow evacuation system for an aircraft engine
US20130087632A1 (en) * 2011-10-11 2013-04-11 Patrick Germain Gas turbine engine exhaust ejector nozzle with de-swirl cascade
WO2016140866A1 (en) 2015-03-04 2016-09-09 Sikorsky Aircraft Corporation Gas turbine exhaust assembly
CN107143533A (en) * 2015-12-07 2017-09-08 张玉良 Save injector

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2467990A1 (en) * 1979-10-22 1981-04-30 United Technologies Corp SILENCER FOR GAS TURBINE
FR2482199A1 (en) * 1980-05-07 1981-11-13 Astech Gas turbine exhaust pipe - has double flow with central pipe having venturi fitted to outer end and included inside final exhaust
US4566270A (en) * 1981-11-03 1986-01-28 Rolls-Royce Limited Gas turbine engine infra-red radiation suppressor
GB2119023A (en) * 1982-04-15 1983-11-09 Secr Defence Jet propulsion nozzle having a shroud
EP1191214A2 (en) * 2000-08-31 2002-03-27 General Electric Company Exhaust nozzle with stub airfoils
EP1191214A3 (en) * 2000-08-31 2004-06-23 General Electric Company Exhaust nozzle with stub airfoils
US7735601B1 (en) 2005-03-15 2010-06-15 Rolls-Royce Plc Engine noise
US7784270B2 (en) 2006-06-19 2010-08-31 Snecma Rotary motion mixer for a converging-stream nozzle of a turbomachine
EP1870588A1 (en) * 2006-06-19 2007-12-26 Snecma Swirling flow mixing nozzle for a turbomachine
FR2967134A1 (en) * 2010-11-04 2012-05-11 Airbus Operations Sas Nacelle for aircraft jet engine, has nozzle and noise reduction device that is arranged at downstream end of nozzle, where intermediate flow is provided between rest of one flow and rest of another flow in area downstream of device
EP2497934A1 (en) * 2011-03-07 2012-09-12 EADS Construcciones Aeronauticas, S.A. Flow evacuation system for an aircraft engine
US20130087632A1 (en) * 2011-10-11 2013-04-11 Patrick Germain Gas turbine engine exhaust ejector nozzle with de-swirl cascade
WO2016140866A1 (en) 2015-03-04 2016-09-09 Sikorsky Aircraft Corporation Gas turbine exhaust assembly
EP3265662A4 (en) * 2015-03-04 2018-10-24 Sikorsky Aircraft Corporation Gas turbine exhaust assembly
US10612421B2 (en) 2015-03-04 2020-04-07 Sikorsky Aircraft Corporation Gas turbine exhaust assembly
CN107143533A (en) * 2015-12-07 2017-09-08 张玉良 Save injector

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