US5143329A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Gas turbine engine powered aircraft environmental control system and boundary layer bleed
Assignee: General Electric Co
•
Filing: 1991-08-01
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Granted: 1992-09-01
•
Expires: 2011-08-01
Abstract
Abstract An aircraft gas turbine engine is provided with a starting air turbine that is directly connected through the starter gearbox to the high pressure (HP) shaft and is provided with an apparatus to extract excess energy from engine compressor bleed air, return it to the engine, and to start the engine with compressed air from starting air sources, and to cool and provide compressed air for powering the Environmental Control System (ECS) and using the bleed air for cabin refreshening. The air turbine may be connected to a nacelle boundary layer bleed compressor to bleed boundary layer air from a forward portion of the nacelle to reduce nacelle surface drag. The ECS may be provided with a wing boundary layer bleed means which uses a cooling air fan in the ECS to draw cooling air through the heat exchangers in the ECS pack from the boundary layer air from a forward portion of the aircraft's wing to reduce its surface drag.
Inventors
- 👤 George A. Coffinberry
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-01 07:01
CPC Classifications
F; F02; F02C; F02C6/00; F02C6/04; F02C6/06; F02C6/08; B; B64; B64C; B64C21/00; B64C21/02; B64C21/06; B64D; B64D13/00; B64D13/06; F02C7/00; F02C7/26; F02C7/268; F02C7/275; F02C7/277; F02C7/32; B64C2230/00; B64C2230/04; B64C2230/06; B64D2013/0603; B64D2013/0622; B64D2013/0648; B64D2013/0659; B64D2013/0696; Y; Y02; Y02T; Y02T50/00; Y02T50/10; Y02T50/50; Y02T50/60
Claims Analysis
Total Claims: 8
Claim 1
Independent Claim
149 words
An environmental control system and aircraft boundary layer bleed system apparatus powered by an aircraft propulsive gas turbine engine, said apparatus comprising: a bleed air means to bleed compressor bleed air from a compressor stage of the gas turbine engine, a starting air turbine in fluid supply communication with said bleed air means effective for extracting energy from the bleed air supplied by said bleed air means and converting the extracted energy to useful work, a work transmission means operably connected to said starting air turbine effective to return the work from said air turbine to the engine, a first bleed duct in fluid supply communication with said energy extraction and work conversion means to supply bleed air exhaust from said air turbine to a means for conditioning cabin air for an aircraft, and at least one means for bleeding boundary layer air form the surface of the aircraft.
Claim 2
Dependent Claim
149 words
An environmental control system and aircraft boundary layer bleed system apparatus powered by an aircraft propulsive gas turbine engine, said apparatus comprising: a bleed air means to bleed compressor bleed air from a compressor stage of the gas turbine engine, a starting air turbine in fluid supply communication with said bleed air means effective for extracting energy from the bleed air supplied by said bleed air means and converting the extracted energy to useful work, a work transmission means operably connected to said starting air turbine effective to return the work from said air turbine to the engine, a first bleed duct in fluid supply communication with said energy extraction and work conversion means to supply bleed air exhaust from said air turbine to a means for conditioning cabin air for an aircraft, and at least one means for bleeding boundary layer air form the surface of the aircraft.
Claim 3
Dependent Claim
63 words
An apparatus as claimed in claim 1 wherein said means for bleeding boundary layer air includes a nacelle boundary layer bleed means comprising; a perforated skin surrounding a forward nacelle portion having a nacelle plenum disposed within; a nacelle bleed duct connecting, in fluid supply communication, said nacelle plenum to an inlet of a boundary layer compressor drivenly linked to said air turbine.
Claim 4
Dependent Claim
51 words
An apparatus as claimed in claim 2 wherein said boundary layer compressor and said air turbine are mounted on a common shaft and said transmission means comprises a shaft means including said common shaft connecting said air turbine in driving relationship through an starter gearbox to a rotor in the engine.
Claim 5
Dependent Claim
70 words
An apparatus as claimed in claim 1 wherein said means for bleeding boundary layer air includes a wing boundary layer bleed means comprising; a perforated skin surrounding a forward wing portion having a wing plenum disposed within; and an Environmental Control System cooling duct connected, in fluid supply communication, said wing plenum to an inlet of an Environmental Control System cooling fan drivenly linked to an Environmental Control System turbine.
Claim 6
Dependent Claim
70 words
An apparatus as claimed in claim 2 wherein said means for bleeding boundary layer air includes a wing boundary layer bleed means comprising; a perforated skin surrounding a forward wing portion having a wing plenum disposed within; and an Environmental Control System cooling duct connected, in fluid supply communication, said wing plenum to an inlet of an Environmental Control System cooling fan drivenly linked to an Environmental Control System turbine.
Claim 7
Dependent Claim
52 words
An apparatus as claimed in claim 2 or claim 3 wherein said nacelle is a tail engine nacelle and said apparatus further comprises a tail assembly boundary layer bleed means including a horizontal stabilizer boundary layer bleed means and vertical stabilizer boundary layer bleed means in fluid communication with said nacelle plenum.
Claim 8
Dependent Claim
60 words
An apparatus as claimed in claim 2 or claim 3 further comprising a low pressure base pressure drag producing region of a fan duct in said gas turbine engine and a means for introducing the boundary layer air bled by said means for bleeding boundary layer air into said low pressure base pressure drag producing region of a fan duct.
References Cited (Backward Citations)
US2734443A
Cited
GB585341A
Cited
US2777301A
Cited
GB743598A
Cited
GB744923A
Cited
GB774695A
Cited
GB846358A
Cited
US3024624A
Cited
US3097817A
Cited
US3428242A
Cited
US3711044A
Cited
US3878677A
Cited
GB1530330A
Cited
US4193262A
Cited
GB2027874A
Cited
GB2074654A
Cited
GB2076897A
Cited
US4419926A
Cited
US4482114A
Cited
EP0065855A1
Cited
EP0076668A2
Cited
US4546939A
Cited
US4462561A
Cited
GB2127492A
Cited
US4503666A
Cited
US4494372A
Cited
US4642997A
Cited
US4666104A
Cited
US4684081A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1995-09-01 | 1996-03-02 | 1996-09-01 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1999-09-01 | 2000-03-02 | 2000-09-01 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2003-09-01 | 2004-03-02 | 2004-09-01 | $7700.00 | Window Closed / Lapsed |