Patent US4903480A successfully refreshed from Google Patents.
US4903480A
Expired / Lapsed
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Hypersonic scramjet engine fuel injector
Assignee: General Electric Co
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Filing: 1988-09-16
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Granted: 1990-02-27
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Expires: 2008-09-16
Abstract
Abstract A hypersonic scramjet engine fuel injector and a hypersonic scramjet engine having such a fuel injector. The engine has a serially connected inlet, combustor, and exhaust nozzle. Multiple, horizontally-spaced-apart fuel injectors are positioned in and connected to the combustor's top portion. Each fuel injector has a hollow wedge shape housing. To improve fuel-air mixing for better combustion, the housing's end wall has multiple, discrete, convergent-divergent fuel outlet nozzles and its side walls have horizontally-extending exterior grooves. Fuel is used to cool the fuel injector housing with the housing's bottom and side walls having fuel-exit holes and the housing having an interior serpentine fuel passageway.
Inventors
- 👤 Ching-Pang Lee
- 👤 Kattalaicheri S. Venkataramani
- 👤 Daniel J. Lahti
- 👤 Vincent H. Lee
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-25 22:04
CPC Classifications
F; F23; F23R; F23R3/00; F23R3/28; F02; F02K; F02K7/00; F02K7/10; F02K9/00; F02K9/42; F02K9/44; F02K9/52; F05; F05D; F05D2260/00; F05D2260/20
Claims Analysis
Total Claims: 8
Claim 1
Independent Claim
104 words
A hypersonic scramjet engine fuel injector comprising a housing having a generally horizontal top wall, an inclined bottom wall, and a generally vertical end wall attached together to define in cross section a generally right triangle, said housing also having two generally vertical side walls having a said-generally-right-triangle shape, said side walls attached to said top, bottom, and end walls to define a fuel-tight, generally right-triangular wedge, said top wall having a fuel inlet orifice, said end wall having at least one convergent-divergent fuel outlet nozzle, and at least one wall of said bottom and side walls having a plurality of spaced-apart fuel-exit holes.
Claim 2
Dependent Claim
104 words
A hypersonic scramjet engine fuel injector comprising a housing having a generally horizontal top wall, an inclined bottom wall, and a generally vertical end wall attached together to define in cross section a generally right triangle, said housing also having two generally vertical side walls having a said-generally-right-triangle shape, said side walls attached to said top, bottom, and end walls to define a fuel-tight, generally right-triangular wedge, said top wall having a fuel inlet orifice, said end wall having at least one convergent-divergent fuel outlet nozzle, and at least one wall of said bottom and side walls having a plurality of spaced-apart fuel-exit holes.
Claim 3
Dependent Claim
33 words
The fuel injector of claim 1, wherein one of said side walls has said fuel-exit holes, said side-wall fuel-exit holes being canted, with respect to said one side wall, toward said end wall.
Claim 4
Dependent Claim
25 words
The fuel injector of claim 1, wherein said bottom wall has said fuel-exit holes, said bottom-wall fuel-exit holes being generally perpendicular to said bottom wall.
Claim 5
Dependent Claim
59 words
The fuel injector of claim 1, wherein said bottom wall has said fuel-exit holes, said fuel injector also including a deflector and a multiplicity of tab members connecting said deflector to said bottom wall so as to leave a space therebetween, said deflector disposed proximate said bottom-wall fuel-exit holes and sized to at least span said bottom-wall fuel-exit holes.
Claim 6
Dependent Claim
18 words
The fuel injector of claim 4, wherein said bottom-wall fuel-exit holes are generally parallel to said top wall.
Claim 7
Dependent Claim
187 words
A hypersonic scramjet engine comprising: (a) an inlet having an inclined upper wall and having an aft portion; (b) a combustor serially connected to said aft portion of said inlet, said combustor having a top portion; (c) an exhaust nozzle serially connected to said combustor; and (d) a plurality of horizontally-spaced-apart fuel injectors disposed in, and connected to said top portion of, said combustor, each said fuel injector including a housing having a generally horizontal top wall, an inclined bottom wall, and a generally vertical end wall attached together to define in cross section a generally right triangle, said housing also having two generally vertical side walls having a said-generally-right-triangle shape, said side walls attached to said top, bottom, and end walls to define a fuel-tight, generally right-triangular wedge, said top wall having a fuel inlet orifice, said end wall having at least one convergent-divergent fuel outlet nozzle, and at least one wall of said bottom and side walls having a plurality of spaced-apart fuel-exit holes, wherein said bottom wall of each said fuel injector is generally coplanar and coextensive with said upper wall of said inlet.
Claim 8
Dependent Claim
187 words
A hypersonic scramjet engine comprising: (a) an inlet having an inclined upper wall and having an aft portion; (b) a combustor serially connected to said aft portion of said inlet, said combustor having a top portion; (c) an exhaust nozzle serially connected to said combustor; and (d) a plurality of horizontally-spaced-apart fuel injectors disposed in, and connected to said top portion of, said combustor, each said fuel injector including a housing having a generally horizontal top wall, an inclined bottom wall, and a generally vertical end wall attached together to define in cross section a generally right triangle, said housing also having two generally vertical side walls having a said-generally-right-triangle shape, said side walls attached to said top, bottom, and end walls to define a fuel-tight, generally right-triangular wedge, said top wall having a fuel inlet orifice, said end wall having at least one convergent-divergent fuel outlet nozzle, and at least one wall of said bottom and side walls having a plurality of spaced-apart fuel-exit holes, wherein said bottom wall of each said fuel injector is generally coplanar and coextensive with said upper wall of said inlet.
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USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1993-02-26 | 1993-08-28 | 1994-02-27 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1997-02-26 | 1997-08-28 | 1998-02-27 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2001-02-26 | 2001-08-28 | 2002-02-27 | $7700.00 | Window Closed / Lapsed |