US4801092A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Injector assembly for a fluid fueled engine
Assignee: Boeing North American Inc
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Filing: 1987-08-31
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Granted: 1989-01-31
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Expires: 2007-08-31
Abstract
Abstract An injector assembly 10 for injecting propellants into a fluid fueled rocket engine. Injection assembly 10 comprises a plate member 12 with an opening 16 therethrough. Injector element 14 is sealed within opening 16. Oxidizer flows through central bore 18 and through orifices 26 into combustion chamber 27. Fuel flows from passageway 34 into an annular manifold 38 formed at an interface between flanged portion 32 and plate member 12. Fuel is then injected through orifices 42 into combustion chamber 27 where it impinges with the oxidizer at predetermined points in the combustion chamber 27.
Inventors
- 👤 William T. Webber
- 👤 Robert M. Saxelby
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-24 10:28
CPC Classifications
F; F23; F23D; F23D11/00; F23D11/36; F23D11/38; B; B05; B05B; B05B7/00; B05B7/02; B05B7/08; B05B7/0807; B05B7/0892; F02; F02K; F02K9/00; F02K9/42; F02K9/44; F02K9/52
Claims Analysis
Total Claims: 11
Claim 1
Independent Claim
267 words
An injector assembly for injecting first and second liquid propellants into a combustion chamber of a fluid fueled rocket engine, comprising: a substantially solid, one-piece flat plate member having an upstream face in fluid communication with a source of said first propellant and a downstream face adjacent a combustion chamber. said plate member having an opening extending therethrough from the upstream face to said downstream face, said opening being enlarged adjacent said downstream face, said plate member further including at least one narrow, straight fluid passageway having a substantially constant cross-sectional flow area for minimizing the volume of the propellants contained therein, said fluid passageway having a first end in fluid communication with a source of said second propellant and a second end in fluid communication with said opening; and a substantially solid injector element located in said opening in said plate member having an outer periphery in sealing engagement therewith, said injector element including a first propellant injection passageway having an upstream end in fluid communication with the source of said first propellant and at least one downstream end in fluid communication with said combustion chamber, said injector element further including a plurality of second propellant injection passageways having diameters in a range between 0.004 and 0.200 inches, each having an upstream end in fluid communication with the second end of said fluid passageway in said plate member and a downstream end in fluid communication with said combustion chamber; said first and second propellant injection passageways being angularly disposed to provide for impingement of said propellants upon one another at predetermined points in said combustion chamber.
Claim 2
Dependent Claim
267 words
An injector assembly for injecting first and second liquid propellants into a combustion chamber of a fluid fueled rocket engine, comprising: a substantially solid, one-piece flat plate member having an upstream face in fluid communication with a source of said first propellant and a downstream face adjacent a combustion chamber. said plate member having an opening extending therethrough from the upstream face to said downstream face, said opening being enlarged adjacent said downstream face, said plate member further including at least one narrow, straight fluid passageway having a substantially constant cross-sectional flow area for minimizing the volume of the propellants contained therein, said fluid passageway having a first end in fluid communication with a source of said second propellant and a second end in fluid communication with said opening; and a substantially solid injector element located in said opening in said plate member having an outer periphery in sealing engagement therewith, said injector element including a first propellant injection passageway having an upstream end in fluid communication with the source of said first propellant and at least one downstream end in fluid communication with said combustion chamber, said injector element further including a plurality of second propellant injection passageways having diameters in a range between 0.004 and 0.200 inches, each having an upstream end in fluid communication with the second end of said fluid passageway in said plate member and a downstream end in fluid communication with said combustion chamber; said first and second propellant injection passageways being angularly disposed to provide for impingement of said propellants upon one another at predetermined points in said combustion chamber.
Claim 3
Dependent Claim
48 words
The injector assembly of claim 1 wherein: the upstream end of said first propellant passageway includes a central bore extending through most of the length of the injector element and branching into a plurality of narrow orifices which extend to the downstream end of said first propellant passageway.
Claim 4
Dependent Claim
114 words
The injector assembly of claim 1 wherein: said plate member is counterbored at the downstream face; and said injector element is substantially cylindrical and includes an outwardly extending flanged portion at the downstream end thereof said flanged portion being contained within said counterbore, said flanged portion having a face with a groove therein; wherein an annular manifold is formed at the interface of said face and said plate member, said manifold including: an inlet in fluid communication with the second end of the fluid passageway in the plate member, and a plurality of outlets in fluid communication with the upstream ends of said plurality of second propellant injection passageways in said said injector element.
Claim 5
Dependent Claim
44 words
The injector assembly of claim 3 wherein: the fluid passageway for second propellant extends partially through said plate member the first end of said fluid passageway connecting to a second manifold within said plate member which is in fluid communication with said second propellant.
Claim 6
Dependent Claim
49 words
The injector assembly of claim 3 wherein: the upstream end of said first propellant passageway includes a central bore extending through most of the length of the injector element and branching into a first plurality of narrow orifices which extend to the downstream end of said first propellant passageway.
Claim 7
Dependent Claim
31 words
The injector assembly of claim 5 wherein: said plurality of second propellant injection passageways includes a second plurality of narrow orifices equidistantly disposed about a central axis of said injector element.
Claim 8
Dependent Claim
63 words
The injector assembly of claim 6 wherein: said second plurality of narrow orifices are equidistantly disposed about the central axis of said injector at a distance from the central axis which is less than the distance that the second plurality of orifices are disposed about the central axis, there being a one-to-one correspondence between each of said first and second plurality of orifices.
Claim 9
Dependent Claim
111 words
The injector assembly of claim 1 wherein: said plate member is counterbored at the downstream face; said injector element is substantially cylindrical and includes an outwardly extending flanged portion at the downstream end thereof, said flanged portion being wider than said counterbore and being positioned downstream of the downstream face of the plate member wherein; said injector element and said plate member cooperatively form an annular manifold, said manifold including: an inlet in fluid communication with the second end of the fluid passageway in the plate member, and a plurality of outlets in fluid communication with the upstream end of said plurality of second propellant injection passageways in said injector element.
Claim 10
Dependent Claim
243 words
In a fluid fueled rocket engine including an injector assembly for injecting first and second liquid propellants into a combustion chamber, the improvement to the injector assembly comprising: a substantially solid one-piece plate member having an upstream face in fluid communication with a source of said first propellant and a downstream face adjacent a combustion chamber, said plate member having an open extending therethrough from the upstream face to said downstream face, said plate member further including a narrow fluid passageway having a first end in fluid communication with a source of said second propellant and a second end in fluid communication with said opening; and a substantially solid injector element located in said opening in said plate member having an outer periphery in sealing engagement therewith, said injector element including a first propellant injection passageway having an upstream end in fluid communication with the source of said first propellant and at least one downstream end in fluid communication with said combustion chamber, said injector element further including a plurality of second propellant injection passageways having diameters in a range between 0.004 and 0.200 inches, each having an upstream end in fluid communication with the second end of said fluid passageway in said plate member and a downstream end in fluid communication with said combustion chamber; said first and second propellant injection passageways being angularly disposed to provide for impingement of said propellants upon one another at predetermined points in said combustion chamber.
Claim 11
Dependent Claim
243 words
In a fluid fueled rocket engine including an injector assembly for injecting first and second liquid propellants into a combustion chamber, the improvement to the injector assembly comprising: a substantially solid one-piece plate member having an upstream face in fluid communication with a source of said first propellant and a downstream face adjacent a combustion chamber, said plate member having an open extending therethrough from the upstream face to said downstream face, said plate member further including a narrow fluid passageway having a first end in fluid communication with a source of said second propellant and a second end in fluid communication with said opening; and a substantially solid injector element located in said opening in said plate member having an outer periphery in sealing engagement therewith, said injector element including a first propellant injection passageway having an upstream end in fluid communication with the source of said first propellant and at least one downstream end in fluid communication with said combustion chamber, said injector element further including a plurality of second propellant injection passageways having diameters in a range between 0.004 and 0.200 inches, each having an upstream end in fluid communication with the second end of said fluid passageway in said plate member and a downstream end in fluid communication with said combustion chamber; said first and second propellant injection passageways being angularly disposed to provide for impingement of said propellants upon one another at predetermined points in said combustion chamber.
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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) | 1992-01-31 | 1992-08-01 | 1993-01-31 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1996-01-31 | 1996-08-01 | 1997-01-31 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2000-01-31 | 2000-08-01 | 2001-01-31 | $7700.00 | Window Closed / Lapsed |