Patent US4879874A successfully refreshed from Google Patents.
US4879874A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Liquid fuel rocket engine
Assignee: National Space Development Agency of Japan
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Filing: 1988-04-18
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Granted: 1989-11-14
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Expires: 2008-04-18
Abstract
Abstract The present invention is related to a liquid fuel rocket engine of the type that a liquid fuel is boosted in pressure by way of a booster means. Thus boosted liquid fuel is gasified with a fuel cooling jacket of a fuel combustor means with an expansion pressure of thus gasified fuel being adapted to energize the booster means, and the gasified fuel is sent to the fuel combustor means so as to be combusted therein to produce a combustion gas to be discharged outwardly serving as a propulsive effort of the rocket engine, wherein there is mounted an expansion nozzle cooling jacket means around the circumference of a high expansion nozzle means of the combustor means, wherein part of the gasified fuel from the combustor cooling jacket means is directed into the expansion nozzle cooling jacket means to be reheated therein resulting in an increased potential energy to be utilized as a potential energy for driving the booster means, and wherein the remaining major part of gasified fuel from the combustor cooling jacket means is fed intact into the combustor means, not utilized to energize the booster means, so that it may be combusted to be discharged as propulsive force, whereby a pressure loss of the gasified fuel is held to a minimum, while establishing a potential energy made available for driving the booster means.
Inventors
- 👤 Yukio Koyari
- 👤 Eiji Sogame
- 👤 Kanji Kishimoto
- 👤 Yojiro Kakuma
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-04 00:48
CPC Classifications
F; F02; F02K; F02K9/00; F02K9/42; F02K9/44; F02K9/46; F02K9/48; F02K9/60; F02K9/62; F02K9/64
Claims Analysis
Total Claims: 4
Claim 1
Independent Claim
350 words
A liquid fuel rocket engine having a fuel booster means (3) for boosting the pressure of fuel component, an oxidizer booster means (4) for boosting the pressure of oxidizer component, two booster driving means for energizing said two booster means, a combustor means (6) wherein said booster fuel and oxidizer components are put into combustion to produce a combustion gas to be discharged outwardly, a combustor cooling jacket means (7) mounted operatively around the circumference of said combustor means, a high expansion nozzle means (8) extending from said combustor means (6), and an expansion nozzle cooling jacket means (9) disposed operatively around the circumference of said high expansion nozzle means (8), said engine having an outlet from said fuel booster means (3) connected operatively to an inlet to said combustor cooling jacket means (7), having an outlet from said combustor cooling jacket means (7) connected operatively to a fuel inlet to said combustor means (6) and to an inlet to said expansion nozzle cooling jacket means (9), and having an outlet from said expansion nozzle cooling jacket means (9) connected operatively to an inlet to said two booster driving means (5), respectively; said engine is characterized in that said expansion nozzle cooling jacket means (9) comprises an alternating arrangement of upflow and downflow tube means (11, 12) along the surface of said high expansion nozzle means (8), said upflow and downflow tube means being connected to each other at their downstream ends (13), said outlet from said combustor cooling jacket means (7) being connected to the downflow tube means (11), and outlets from said upflow tube means (12) being connected to an inlet to one of said booster driving means (5), said engine being further characterized in that a non-cooled nozzle extension means (14) is disposed in the downstream position from said expansion nozzle cooling jacket means (9) and a turbine exhaust gas manifold means (15) is disposed in said non-cooled nozzle extension means (14), said turbine exhaust gas manifold means (I5) being connected to one of said booster driving means (5) through a turbine exhaust gas duct means (16).
Claim 2
Dependent Claim
350 words
A liquid fuel rocket engine having a fuel booster means (3) for boosting the pressure of fuel component, an oxidizer booster means (4) for boosting the pressure of oxidizer component, two booster driving means for energizing said two booster means, a combustor means (6) wherein said booster fuel and oxidizer components are put into combustion to produce a combustion gas to be discharged outwardly, a combustor cooling jacket means (7) mounted operatively around the circumference of said combustor means, a high expansion nozzle means (8) extending from said combustor means (6), and an expansion nozzle cooling jacket means (9) disposed operatively around the circumference of said high expansion nozzle means (8), said engine having an outlet from said fuel booster means (3) connected operatively to an inlet to said combustor cooling jacket means (7), having an outlet from said combustor cooling jacket means (7) connected operatively to a fuel inlet to said combustor means (6) and to an inlet to said expansion nozzle cooling jacket means (9), and having an outlet from said expansion nozzle cooling jacket means (9) connected operatively to an inlet to said two booster driving means (5), respectively; said engine is characterized in that said expansion nozzle cooling jacket means (9) comprises an alternating arrangement of upflow and downflow tube means (11, 12) along the surface of said high expansion nozzle means (8), said upflow and downflow tube means being connected to each other at their downstream ends (13), said outlet from said combustor cooling jacket means (7) being connected to the downflow tube means (11), and outlets from said upflow tube means (12) being connected to an inlet to one of said booster driving means (5), said engine being further characterized in that a non-cooled nozzle extension means (14) is disposed in the downstream position from said expansion nozzle cooling jacket means (9) and a turbine exhaust gas manifold means (15) is disposed in said non-cooled nozzle extension means (14), said turbine exhaust gas manifold means (I5) being connected to one of said booster driving means (5) through a turbine exhaust gas duct means (16).
Claim 3
Dependent Claim
39 words
The liquid fuel rocket engine of claim 1, wherein said engine is further characterized in that a direct cooling line means (17) is disposed between said liquid fuel booster means (3) and said expansion nozzle cooling jacket means (9).
Claim 4
Dependent Claim
53 words
The liquid fuel rocket engine of claim 1, wherein said engine is further characterized in that a turbine gas bleed line means (18) is disposed between said turbine exhaust gas duct means (16) and a duct means connecting said expansion nozzle cooling jacket means (9) to one of said booster driving means (5).
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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) | 1992-11-13 | 1993-05-15 | 1993-11-14 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1996-11-13 | 1997-05-15 | 1997-11-14 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2000-11-13 | 2001-05-15 | 2001-11-14 | $7700.00 | Window Closed / Lapsed |