Core flow expansion chamber device system for reduction of jet t

Power plants – Reaction motor – Interrelated reaction motors

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60262, 181213, 181217, 181220, 23926513, F02K 100, F02K 304

Patent

active

057584885

ABSTRACT:
A noise reduction system is provided for installation on a bypass turbine having a core engine, an outer casing and a thrust reverser. The system is comprised of an acoustically treated nose cowl conventional for the engine; a respaced inlet guide vane upstream of the core engine for reducing wake disturbances striking the engine fan; a flow diverter downstream of the core engine for turning fan air inward toward the engine center line and for turning core air outward; a structure for supporting and positioning said flow diverter relative to the engine; a core flow expansion chamber device for slowing the peak velocity of the exhaust gas prior to exhausting it to the atmosphere; and an acoustic tailpipe assembly configured to define an outlet area sized and shaped to compensate for the mass flow loss created by the core flow expansion chamber device.

REFERENCES:
patent: 2931171 (1960-04-01), Tyler et al.
patent: 2934889 (1960-05-01), Poulos
patent: 2940252 (1960-06-01), Reinhart
patent: 2943444 (1960-07-01), Baxter
patent: 2988302 (1961-06-01), Smith
patent: 3061038 (1962-10-01), Lawler et al.
patent: 3062818 (1962-11-01), Schaefer et al.
patent: 3065818 (1962-11-01), Lombard et al.
patent: 3174282 (1965-03-01), Harrison
patent: 3227240 (1966-01-01), Lee et al.
patent: 3289413 (1966-12-01), Gist, Jr.
patent: 3455413 (1969-07-01), Henley
patent: 3508403 (1970-04-01), Neitzel
patent: 3542152 (1970-11-01), Adamson et al.
patent: 3579993 (1971-05-01), Tanner
patent: 3598318 (1971-08-01), Schiel
patent: 3696617 (1972-10-01), Ellis
patent: 3710890 (1973-01-01), True et al.
patent: 3819009 (1974-06-01), Motsinger
patent: 3886737 (1975-06-01), Grieb
patent: 3893640 (1975-07-01), Hull, Jr.
patent: 3954224 (1976-05-01), Colebrook et al.
patent: 3982696 (1976-09-01), Gordon
patent: 4003249 (1977-01-01), Laskody
patent: 4030291 (1977-06-01), Sargisson
patent: 4045957 (1977-09-01), DiSabato
patent: 4077206 (1978-03-01), Ayyagari
patent: 4086761 (1978-05-01), Schaut et al.
patent: 4117671 (1978-10-01), Neal et al.
patent: 4127756 (1978-11-01), Peterson et al.
patent: 4135363 (1979-01-01), Packman
patent: 4137992 (1979-02-01), Herman
patent: 4149375 (1979-04-01), Wynosky et al.
patent: 4165609 (1979-08-01), Rudolph
patent: 4215536 (1980-08-01), Rudolph
patent: 4217756 (1980-08-01), Laskody
patent: 4226085 (1980-10-01), Johnson
patent: 4227370 (1980-10-01), Kirker
patent: 4235303 (1980-11-01), Dhoore et al.
patent: 4240252 (1980-12-01), Sargisson et al.
patent: 4244441 (1981-01-01), Tolman
patent: 4289984 (1981-09-01), Bhat et al.
patent: 4291782 (1981-09-01), Klees
patent: 4292803 (1981-10-01), Prior
patent: 4335573 (1982-06-01), Wright
patent: 4384634 (1983-05-01), Shuttleworth
patent: 4401269 (1983-08-01), Eiler
patent: 4422524 (1983-12-01), Osborn
patent: 4433751 (1984-02-01), Bonneau
patent: 4449607 (1984-05-01), Forestier et al.
patent: 4452335 (1984-06-01), Mathews et al.
patent: 4501393 (1985-02-01), Klees et al.
patent: 4516660 (1985-05-01), Greenlaw
patent: 4696159 (1987-09-01), Horgan
patent: 4723626 (1988-02-01), Carr et al.
patent: 4751979 (1988-06-01), Wiseman
patent: 4754924 (1988-07-01), Shannon
patent: 4759513 (1988-07-01), Birbragher
patent: 4836469 (1989-06-01), Wagenfeld
patent: 4909346 (1990-03-01), Torkelson
patent: 4979587 (1990-12-01), Hirt et al.
patent: 5014815 (1991-05-01), Arcas et al.
patent: 5058703 (1991-10-01), Ealba et al.
patent: 5127602 (1992-07-01), Batey et al.
patent: 5133194 (1992-07-01), Army, Jr.
patent: 5154052 (1992-10-01), Giffin et al.
patent: 5157916 (1992-10-01), Wynosky et al.
patent: 5167118 (1992-12-01), Torkelson
Bernhard H. Goethert, Noise Attenuation and Associated Thrust Increase of Turbojet Engines Through Hyper-Mixing Ejector Shrouds, Fifth International Symposium on Air Breathing Engines: Symposium Papers 17-1 (1981).
F.H. Pond and R.A. Heinz, JT8D Engine Internal Exhaust Mixer Technology Program: Final Report, Rpt. No. FAA-80-69 (1980) (prepared for U.S. Dept. of Transportation, Federal Aviation Administration).
F.G. Strout and A. Atencio Jr., Flight Effects on Noise Generated by a JT8D Engine with Inverted Primary/Fan Flow, Journal of Aircraft, Jan. 1980, at 13.
General Electric Co., High Velocity Jet Noise Source Location and Reduction: Task 6--Noise Abatement Nozzle Design Guide, Rpt. No. FAA-RD-76-79 (1979) (prepared for Dept. of Transportation, Federal Aviation Administration).
General Electric Co., High Velocity Jet Noise Source Location and Reduction: Task 2--Theoretical Developments and Basic Experiments, Rpt. No. FAA-RD-76-79 (1978) (prepared for Dept. of Transportation, Federal Aviation Administration).
A.B. Packman and D.C. Eiler, Internal Mixer Investigation for JT8D Engine Jet Noise Reduction, Rpt. No. FAA-RD-77-132 (1977) (prepared for Dept. of Transportation, Federal Aviation Administration).
Nordman JT-8 Hushkit, Flight International, Aug. 1990, at 6 (photograph of a new product).
News Briefs, Aviation Week, May 2, 1988, at 34 (announcing Pratt & Whitney hush kit using mixer).
Airline Observer, Aviation Week, Oct. 3, 1988, at 13 (announcing Quiet Nacelle Corp. JT8D hush kit).
David Woolley, Hush-kit Manufacturers Scramble to Equip Older Jets, Interavia, Jun. 1985, at 634.

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