GB935119A - Improvements relating to the silencing of gas turbine engines - Google Patents

Improvements relating to the silencing of gas turbine engines

Info

Publication number
GB935119A
GB935119A GB4180860A GB4180860A GB935119A GB 935119 A GB935119 A GB 935119A GB 4180860 A GB4180860 A GB 4180860A GB 4180860 A GB4180860 A GB 4180860A GB 935119 A GB935119 A GB 935119A
Authority
GB
United Kingdom
Prior art keywords
wall
resonance chambers
gas turbine
air inlet
resonance
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
GB4180860A
Inventor
Lindsay Grahame Dawson
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 GB4180860A priority Critical patent/GB935119A/en
Priority to FR880766A priority patent/FR1307475A/en
Publication of GB935119A publication Critical patent/GB935119A/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
    • F02K1/78—Other construction of jet pipes
    • F02K1/82—Jet pipe walls, e.g. liners
    • F02K1/827—Sound absorbing structures or liners

Abstract

935,119. Gas turbine engines; jet propulsion plant. ROLLS-ROYCE Ltd. Nov. 27, 1961 [Dec. 5, 1960], No. 41808/60. Class 110 (3). A gas turbine engine comprises an air intake, a by-pass duct or an exhaust duct which is provided with at least one resonance chamber which substantially reduces or prevents the transmission outwardly thereof of sound waves having a predetermined wavelength or wavelengths. The gas turbine engine shown in Fig. 1 has an air intake 10 around the wall of which is disposed an annular arrangement of resonance chambers 16, each chamber communicating with the air intake. The intake is also provided with series of ring members 17, 18, 19, each of which is also formed with resonance chambers 16. The noise which it is desirable to silence has a frequency of from 1,000 to 15,000 cycles per second. The jet pipe 14 of the engine shown in Fig. 1 is also provided with an annular assembly of resonance chambers 16. The inner fairing cone 20 is likewise provided with resonance chambers and further resonance chambers 16 are provided in the supporting struts 21. A section through the outer wall and the wall of the inner fairing member is shown in Fig. 5, the outer wall comprising spaced skins 23, 24, the space between which is sub-divided into resonance chambers 25, each chamber communicating with the air inlet duct by means of a hole 26. The wall of the fairing member is similarly formed of two skins 30, 31, the space between which is subdivided into resonance chambers 32, each of which communicates with the air inlet duct by means of a hole 33. In a further embodiment, Fig. 7, the air inlet is divided by a number of partitions 35, each of which comprises a pair of spaced walls and an intermediate wall therebetween, the spaces therebetween being subdivided into resonance chambers, each of which communicates with the air inlet duct by means of a hole in the outer wall thereof.
GB4180860A 1960-12-05 1960-12-05 Improvements relating to the silencing of gas turbine engines Expired GB935119A (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
GB4180860A GB935119A (en) 1960-12-05 1960-12-05 Improvements relating to the silencing of gas turbine engines
FR880766A FR1307475A (en) 1960-12-05 1961-12-02 Improvements to noise reduction of turbo-reactors

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB4180860A GB935119A (en) 1960-12-05 1960-12-05 Improvements relating to the silencing of gas turbine engines

Publications (1)

Publication Number Publication Date
GB935119A true GB935119A (en) 1963-08-28

Family

ID=10421459

Family Applications (1)

Application Number Title Priority Date Filing Date
GB4180860A Expired GB935119A (en) 1960-12-05 1960-12-05 Improvements relating to the silencing of gas turbine engines

Country Status (1)

Country Link
GB (1) GB935119A (en)

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3437173A (en) * 1966-11-25 1969-04-08 Gen Electric Gas turbine engine with screech attenuating means
US3477231A (en) * 1967-12-26 1969-11-11 Gen Electric Noise reduction
US3563340A (en) * 1968-02-29 1971-02-16 Bertin & Cie Retractable silencing flaps for jet engine intake
US3568790A (en) * 1969-09-29 1971-03-09 Rohr Corp Air divider ring structure for jet engine inlet air duct
US3666043A (en) * 1970-11-12 1972-05-30 Rohr Corp Air divider ring structure for jet engine inlet air duct
US3693750A (en) * 1970-09-21 1972-09-26 Minnesota Mining & Mfg Composite metal structure useful in sound absorption
US3710889A (en) * 1969-04-23 1973-01-16 Snecma Attenuation of noise from air or gas intake ducts, more especially in aircraft jet turbine engines
US3737005A (en) * 1971-10-14 1973-06-05 Rohr Corp Thrust augmenting and sound suppressing apparatus
US4137992A (en) * 1976-12-30 1979-02-06 The Boeing Company Turbojet engine nozzle for attenuating core and turbine noise
US4258822A (en) * 1979-07-27 1981-03-31 United Technologies Corporation Muffler plug for gas turbine power plant
US4507660A (en) * 1982-07-16 1985-03-26 Advanced Electromagnetics, Inc. Anechoic chamber
GB2271387A (en) * 1992-05-29 1994-04-13 Deutsche Aerospace Noise reduction by sound wave interference.

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3437173A (en) * 1966-11-25 1969-04-08 Gen Electric Gas turbine engine with screech attenuating means
US3477231A (en) * 1967-12-26 1969-11-11 Gen Electric Noise reduction
US3563340A (en) * 1968-02-29 1971-02-16 Bertin & Cie Retractable silencing flaps for jet engine intake
US3710889A (en) * 1969-04-23 1973-01-16 Snecma Attenuation of noise from air or gas intake ducts, more especially in aircraft jet turbine engines
US3568790A (en) * 1969-09-29 1971-03-09 Rohr Corp Air divider ring structure for jet engine inlet air duct
US3693750A (en) * 1970-09-21 1972-09-26 Minnesota Mining & Mfg Composite metal structure useful in sound absorption
US3666043A (en) * 1970-11-12 1972-05-30 Rohr Corp Air divider ring structure for jet engine inlet air duct
US3737005A (en) * 1971-10-14 1973-06-05 Rohr Corp Thrust augmenting and sound suppressing apparatus
US4137992A (en) * 1976-12-30 1979-02-06 The Boeing Company Turbojet engine nozzle for attenuating core and turbine noise
US4258822A (en) * 1979-07-27 1981-03-31 United Technologies Corporation Muffler plug for gas turbine power plant
US4507660A (en) * 1982-07-16 1985-03-26 Advanced Electromagnetics, Inc. Anechoic chamber
GB2271387A (en) * 1992-05-29 1994-04-13 Deutsche Aerospace Noise reduction by sound wave interference.
GB2271387B (en) * 1992-05-29 1995-08-16 Deutsche Aerospace Noise reduction by means of acoustic feedback

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