US4055041A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Integrated gas turbine engine-nacelle
Assignee: National Aeronautics and Space Administration
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Filing: 1975-11-03
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Granted: 1977-10-25
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Expires: 1995-11-03
Abstract
Abstract A nacelle for use with a gas turbine engine is provided with an integral webbed structure resembling a spoked wheel for rigidly interconnecting the nacelle and engine. The nacelle is entirely supported in its spacial relationship with the engine by means of the webbed structure. The inner surface of the nacelle defines the outer limits of the engine motive fluid flow annulus while the outer surface of the nacelle defines a steamlined envelope for the engine.
Inventors
- 👤 Arthur P. Adamson
- 👤 Donald F. Sargisson
- 👤 Charles L. Stotler, Jr.
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-04 18:21
CPC Classifications
B; B64; B64D; B64D29/00; B64D27/00; B64D27/02; B64D27/16; B64D27/18; F; F01; F01D; F01D11/00; F01D11/08; F02; F02C; F02C7/00; F02C7/20; Y; Y02; Y02T; Y02T50/00; Y02T50/40; Y02T50/60
Claims Analysis
Total Claims: 7
Claim 1
Independent Claim
173 words
An integrated propulsion system comprising: a pylon; a gas turbofan engine including a core engine for rotatably driving a fan stage to pressurize a motive fluid, a fan bypass flow annulus generally circumscribing said core engine, a core engine inlet duct communicating with said bypass duct, a flow splitter for separating the fan motive fluid into a bypass portion and a core engine portion, an integral composite frame having first and second generally concentric hoop means of bonded composite filament fabrication interconnected by generally radially extending outer struts of composite filament fabrication bonded thereto, said first hoop means substantially spanning said flow splitter and said second hoop means sandwiched between inner and outer walls of composite filament fabrication bonded thereto, said inner wall defining an outer aerodynamic contour of the turbofan engine, and wherein said inner wall, said outer wall and said second hoop means form a shroud entirely supported in spacial relationship with said first hoop means through said outer struts; and mounting means connecting said first hoop means to said pylon.
Claim 2
Dependent Claim
173 words
An integrated propulsion system comprising: a pylon; a gas turbofan engine including a core engine for rotatably driving a fan stage to pressurize a motive fluid, a fan bypass flow annulus generally circumscribing said core engine, a core engine inlet duct communicating with said bypass duct, a flow splitter for separating the fan motive fluid into a bypass portion and a core engine portion, an integral composite frame having first and second generally concentric hoop means of bonded composite filament fabrication interconnected by generally radially extending outer struts of composite filament fabrication bonded thereto, said first hoop means substantially spanning said flow splitter and said second hoop means sandwiched between inner and outer walls of composite filament fabrication bonded thereto, said inner wall defining an outer aerodynamic contour of the turbofan engine, and wherein said inner wall, said outer wall and said second hoop means form a shroud entirely supported in spacial relationship with said first hoop means through said outer struts; and mounting means connecting said first hoop means to said pylon.
Claim 3
Dependent Claim
55 words
The propulsion system of claim 1 further comprising third hoop means of bonded filament fabrication disposed within and connected to said core engine, and further connected to said first hoop means by a plurality of inner struts of composite filament fabrication, said inner struts supporting said core engine and flow splitter in predetermined spacial relationship.
Claim 4
Dependent Claim
61 words
The propulsion system of claim 1 wherein said mounting means includes: a forward pylon mount attached to an engine hanger associated with said second hoop means; and a thrust mount comprising a rear pylon mount operatively connected to a forward engine mount associated with the first hoop means and further connected to a rear engine mount associated with the core engine.
Claim 5
Dependent Claim
33 words
The propulsion system of claim 3 wherein said rear pylon mount is operatively connected through a pair of thrust rods to two circumferentially spaced forward engine mounts attached to the first hoop means.
Claim 6
Dependent Claim
73 words
The propulsion system of claim 3 further including: engine accessories driven by said core engine; and pull shaft means for operatively connecting said accessories and said core engine; wherein said engine accessories are substantially mounted within a pocket in the pylon; and said shaft means is disconnected from said accessories when said turbofan engine is dismounted from said pylon and connected to said accessories when said turbofan engine is mounted on said pylon.
Claim 7
Dependent Claim
56 words
The propulsion system of claim 3 further including: engine accessories and wherein said engine accessories are mounted upon said turbofan engine outer wall and are disposed within a pocket formed within said pylon when said turbofan engine is mounted thereon, and when said turbofan engine is dismounted from said pylon, said accessories are removed contemporaneous therewith.
References Cited (Backward Citations)
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1980-10-24 | 1981-04-25 | 1981-10-25 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1984-10-24 | 1985-04-25 | 1985-10-25 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1988-10-24 | 1989-04-25 | 1989-10-25 | $7700.00 | Window Closed / Lapsed |