Patent US4841723A successfully refreshed from Google Patents.
US4841723A
Expired / Lapsed
US
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Multiple-propellant air vehicle and propulsion system
Assignee: General Electric Co
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Filing: 1986-10-14
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Granted: 1989-06-27
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Expires: 2006-10-14
Abstract
Abstract A propulsion system and method having means for cooling the combustor liner and throat liner of a rocket casing by endothermic pyrolysis of a hydrocarbon fuel in the fuel passageway which is adjacent to and surrounding the combustor liner and the throat liner. Means is provided for high heat flux to the combustor liner and throat liner from combustion within the rocket casing whereby the temperature of the liners exceeds their thermal limits. Catalyst means are utilized for the endothermic pyrolysis. Hydrocarbon fuel is passed through the fuel passageway; heat is provided from the combustion of fuel in the combustion chamber to the fuel passageway by radiation through the combustor liner and the throat liner; and the hydrocarbon fuel is heated at a temperature sufficient to cause the endothermic pyrolysis of the hydrocarbon in the fuel passageway. By the propulsion system and method, heat is removed from the combustion chamber through the combustion liner and throat liner, and the temperature in the combustion chamber is reduced at the combustor liner and throat liner so that the thermal limit of the combustor liner and throat liner is not exceeded. The endothermic pyrolysis of the hydrocarbon fuel produces an improved fuel product which has a higher combustion rate, a higher combustion temperature and/or results in a fuel product having a lower molecular weight than the hydrocarbon fuel.
Inventors
- 👤 Monica M. Lau
- 👤 George A. Coffinberry
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-30 12:20
CPC Classifications
F; F02; F02K; F02K9/00; F02K9/42; F02K9/60; F02K9/62; F02K9/64; F02K9/68
Claims Analysis
Total Claims: 30
Claim 1
Independent Claim
147 words
A propulsion system which utilizes a hydrocarbon fuel comprising: (a) a rocket casing having a combustor chamber with a combustor liner and a nozzle throat chamber with a nozzle throat liner, whereby the combustor liner and nozzle throat liner provide high heat flux from combustion within the rocket casing and the temperature of the liners exceeds the thermal limits thereof: (b) a fuel passageway for the hydrocarbon fuel adjacent to and surrounding the combustor liner and the nozzle throat liner; (c) a source of hydrocarbon fuel of the type having a freezing point of about 150° R. to about 200° R. and a boiling point of about 275° R. to about 425° R.; and (d) means for providing fuel flow of the hydrocarbon fuel in the fuel passageway; whereby the combustor liner and throat liner are cooled by endothermic pyrolysis of the hydrocarbon in the fuel passageway.
Claim 2
Dependent Claim
147 words
A propulsion system which utilizes a hydrocarbon fuel comprising: (a) a rocket casing having a combustor chamber with a combustor liner and a nozzle throat chamber with a nozzle throat liner, whereby the combustor liner and nozzle throat liner provide high heat flux from combustion within the rocket casing and the temperature of the liners exceeds the thermal limits thereof: (b) a fuel passageway for the hydrocarbon fuel adjacent to and surrounding the combustor liner and the nozzle throat liner; (c) a source of hydrocarbon fuel of the type having a freezing point of about 150° R. to about 200° R. and a boiling point of about 275° R. to about 425° R.; and (d) means for providing fuel flow of the hydrocarbon fuel in the fuel passageway; whereby the combustor liner and throat liner are cooled by endothermic pyrolysis of the hydrocarbon in the fuel passageway.
Claim 3
Dependent Claim
41 words
The propulsion system of claim 1 further comprising catalyst means for endothermic pyrolysis of the hydrocarbon fuel having a freezing point of about 150° R. to about 200° R. and a boiling point of about 275° R. to about 425° R.
Claim 4
Dependent Claim
18 words
The propulsion system of claim 2 wherein the catalyst means is a catalyst bed in the fuel passageway.
Claim 5
Dependent Claim
20 words
The propulsion system of claim 2 wherein the catalyst is a catalyst coated on a wall in the fuel passageway.
Claim 6
Dependent Claim
16 words
The propulsion system of claim 2 wherein the catalyst is a catalyst in the hydrocarbon fuel.
Claim 7
Dependent Claim
63 words
The propulsion system of claims 1, 2, 3, 4 or 5 wherein the hydrocarbon fuel comprises a hydrocarbon, the endothermic pyrolysis of which provides an improved fuel product with at least one of the properties selected from the group consisting of a fuel product having higher combustion rates, a fuel product having higher combustion temperatures and a fuel product yielding lower molecular weight.
Claim 8
Dependent Claim
26 words
The propulsion system of claims 1, 2, 3, 4 or 5 wherein the hydrocarbon is ethylene, and the products of endothermic pyrolysis comprise acetylene and hydrogen.
Claim 9
Dependent Claim
27 words
The propulsion system of claims 1, 2, 3, 4 or 5 wherein the hydrocarbon is ethane, and the products of endothermic pyrolysis comprise methane, acetylene and hydrogen.
Claim 10
Dependent Claim
29 words
The propulsion system of claims 1, 2, 3, 4 or 5 wherein the hydrocarbon is propylene, and the products of endothermic pyrolysis comprise methane, ethane, ethylene, acetylene and hydrogen.
Claim 11
Dependent Claim
30 words
The propulsion system of claims 1, 2, 3, 4 and 5 wherein the hydrocarbon is propane, and the products of endothermic pyrolysis comprise methane, ethane, ethylene, acetylene, propylene and hydrogen.
Claim 12
Independent Claim
180 words
A method of improving the fuel system of a propulsion system having a rocket casing with a combustion chamber having a combustor liner and an exhaust gas throat having a throat liner with a fuel passageway adjacent to and surrounding the combustor liner and the throat liner, comprising: (a) passing a hydrocarbon fuel selected from the group of hydrocarbons having a freezing point of about 150° R. to about 200° R. and a boiling point of about 275° R. to about 425° R. through the fuel passageway; and (b) providing heat from the combustion of fuel in the combustion chamber to the fuel passageway by radiation through the combustor liner and the throat liner; whereby the hydrocarbon fuel is heated at a temperature sufficient to cause the endothermic pyrolysis of the hydrocarbon in the fuel passageway, and the heat removed from the combustion chamber through the combustor liner and throat liner reduces the temperature in the combustion chamber at the combustor liner and the throat liner so the thermal limits of the combustor liner and throat liner are not exceeded.
Claim 13
Independent Claim
180 words
A method of improving the fuel system of a propulsion system having a rocket casing with a combustion chamber having a combustor liner and an exhaust gas throat having a throat liner with a fuel passageway adjacent to and surrounding the combustor liner and the throat liner, comprising: (a) passing a hydrocarbon fuel selected from the group of hydrocarbons having a freezing point of about 150° R. to about 200° R. and a boiling point of about 275° R. to about 425° R. through the fuel passageway; and (b) providing heat from the combustion of fuel in the combustion chamber to the fuel passageway by radiation through the combustor liner and the throat liner; whereby the hydrocarbon fuel is heated at a temperature sufficient to cause the endothermic pyrolysis of the hydrocarbon in the fuel passageway, and the heat removed from the combustion chamber through the combustor liner and throat liner reduces the temperature in the combustion chamber at the combustor liner and the throat liner so the thermal limits of the combustor liner and throat liner are not exceeded.
Claim 14
Dependent Claim
58 words
The method of claim 11 further comprising heating the hydrocarbon fuel in the presence of a catalyst at a temperature sufficient to cause the endothermic pyrolysis of the hydrocarbon fuel having a freezing point of about 150° R. to about 200° R. and a boiling point of about 275° R. to about 425° R. in the fuel passageway.
Claim 15
Dependent Claim
23 words
The method of claim 11 comprising heating the hydrocarbon fuel in the presence of catalyst in a catalyst bed in the fuel passageway.
Claim 16
Dependent Claim
23 words
The method of claim 11 comprising heating the hydrocarbon fuel in the presence of catalyst coated on a wall of the fuel passageway.
Claim 17
Dependent Claim
19 words
The method of claim 11 comprising heating the hydrocarbon fuel in the presence of catalyst incorporated in the fuel.
Claim 18
Independent Claim
69 words
The method of claims 11, 12, 13, 14 or 15 comprising passing a hydrocarbon fuel, the endothermic pyrolysis of which provides an improved fuel product with at least one of the properties selected from the group consisting of a fuel product having higher combustion rates, a fuel product having higher combustion temperatures and a fuel product yielding a lower molecular weight than the hydrocarbon fuel, through the fuel passageway.
Claim 19
Independent Claim
28 words
The method of claims 11, 12, 13, 14 or 15 comprising passing ethylene, the products of endothermic pyrolysis of which comprise acetylene and hydrogen, through the fuel passageway.
Claim 20
Independent Claim
29 words
The method of claims 11, 12, 13, 14 or 15 comprising passing ethane, the products of endothermic pyrolysis of which comprise methane, acetylene and hydrogen, through the fuel passageway.
Claim 21
Independent Claim
30 words
The method of claims 11, 12, 13, 14 or 15 comprising passing propylene, the products of endothermic pyrolysis of which comprise methane, ethane, acetylene and hydrogen, through the fuel passageway.
Claim 22
Independent Claim
32 words
The method of claims 11, 12, 13, 14 or 15 comprising passing propane, the products of endothermic pyrolysis of which comprise methane, ethane, ethylene, acetylene, propylene and hydrogen, through the fuel passageway.
Claim 23
Independent Claim
27 words
The method of claims 11, 12, 13, 14 or 15 wherein the hydrocarbon fuel is heated at a temperature of about 1700° F. to about 2000° F.
Claim 24
Dependent Claim
200 words
A propulsion system which utilizes a hydrocarbon fuel, comprising: (a) a rocket casing having a combustor chamber with a combustor liner and a nozzle throat chamber with a nozzle throat liner, whereby the combustor liner and nozzle throat liner provide high heat flux from combustion within the rocket casing and the temperature of the liners would exceed their thermal limits if not cooled; (b) a fuel passageway for the hydrocarbon fuel adjacent to and surrounding the combustor liner and the nozzle throat liner; (c) a source of hydrocarbon fuel of the type having a freezing point of about 150° R. to about 200° R. and a boiling point of about 275° R. to about 425° R.; (d) means for providing fuel flow of the hydrocarbon fuel in the fuel passageway; and (e) a plurality of flow directing vanes disposed in the fuel passageway to direct the fuel in the fuel passageway circumferentially whereby the fuel travels a longer path through the passageway and thereby increases the residence time of fuel in the passageway; endothermic pyrolysis of the hydrocarbon fuel occurs; and the combustor liner and throat liner are cooled by the endothermic pyrolysis of the hydrocarbon in the fuel passageway.
Claim 25
Dependent Claim
200 words
A propulsion system which utilizes a hydrocarbon fuel, comprising: (a) a rocket casing having a combustor chamber with a combustor liner and a nozzle throat chamber with a nozzle throat liner, whereby the combustor liner and nozzle throat liner provide high heat flux from combustion within the rocket casing and the temperature of the liners would exceed their thermal limits if not cooled; (b) a fuel passageway for the hydrocarbon fuel adjacent to and surrounding the combustor liner and the nozzle throat liner; (c) a source of hydrocarbon fuel of the type having a freezing point of about 150° R. to about 200° R. and a boiling point of about 275° R. to about 425° R.; (d) means for providing fuel flow of the hydrocarbon fuel in the fuel passageway; and (e) a plurality of flow directing vanes disposed in the fuel passageway to direct the fuel in the fuel passageway circumferentially whereby the fuel travels a longer path through the passageway and thereby increases the residence time of fuel in the passageway; endothermic pyrolysis of the hydrocarbon fuel occurs; and the combustor liner and throat liner are cooled by the endothermic pyrolysis of the hydrocarbon in the fuel passageway.
Claim 26
Dependent Claim
28 words
The propulsion system of claim 22 wherein the flow directing vanes disposed in the fuel passageway are swirl vanes attached to the outer wall of the fuel passageway.
Claim 27
Dependent Claim
21 words
The propulsion system of claim 22 wherein the flow directing vanes are disposed in the fuel passageway adjacent the combustor chamber.
Claim 28
Dependent Claim
22 words
The propulsion system of claim 22 wherein the flow directing vanes are disposed in the fuel passageway adjacent the nozzle throat chamber.
Claim 29
Independent Claim
235 words
A method of improving the fuel system of a propulsion system having a rocket casing with a combustor chamber having a combustor liner and an exhaust gas throat having a throat liner with a fuel passageway adjacent to and surrounding the combustor liner and the throat liner, comprising: (a) passing a hydrocarbon fuel selected from the group of hydrocarbons having a freezing point of about 150° R. to about 200° R. and a boiling point of about 275° R. to about 425° R. through the fuel passageway; (b) providing heat from the combustion of fuel in the combustion chamber to the fuel passageway by radiation through the combustor liner and the throat liner; and (c) increasing the residence time of fuel in the fuel passageway by a plurality of flow directing vanes disposed in the fuel passageway to direct the fuel in the fuel passageway circumferentially, the fuel traveling a longer path through the passageway to increase the residence time therein, whereby the hydrocarbon fuel is heated at a temperature sufficient to cause the endothermic pyrolysis of the hydrocarbon in the fuel passageway, and the heat removed from the combustion chamber through the combustor liner and throat liner, causing the endothermic pyrolysis of the hydrocarbon fuel, reduces the temperature in the combustion chamber at the combustor liner and the throat liner so the thermal limits of the combustor liner and throat liner are not exceeded.
Claim 30
Independent Claim
235 words
A method of improving the fuel system of a propulsion system having a rocket casing with a combustor chamber having a combustor liner and an exhaust gas throat having a throat liner with a fuel passageway adjacent to and surrounding the combustor liner and the throat liner, comprising: (a) passing a hydrocarbon fuel selected from the group of hydrocarbons having a freezing point of about 150° R. to about 200° R. and a boiling point of about 275° R. to about 425° R. through the fuel passageway; (b) providing heat from the combustion of fuel in the combustion chamber to the fuel passageway by radiation through the combustor liner and the throat liner; and (c) increasing the residence time of fuel in the fuel passageway by a plurality of flow directing vanes disposed in the fuel passageway to direct the fuel in the fuel passageway circumferentially, the fuel traveling a longer path through the passageway to increase the residence time therein, whereby the hydrocarbon fuel is heated at a temperature sufficient to cause the endothermic pyrolysis of the hydrocarbon in the fuel passageway, and the heat removed from the combustion chamber through the combustor liner and throat liner, causing the endothermic pyrolysis of the hydrocarbon fuel, reduces the temperature in the combustion chamber at the combustor liner and the throat liner so the thermal limits of the combustor liner and throat liner are not exceeded.
References Cited (Backward Citations)
GB459924A
Cited
US2655786A
Cited
GB727720A
Cited
GB793300A
Cited
US2902822A
Cited
US2940253A
Cited
FR1108090A
Cited
US2974475A
Cited
US2952969A
Cited
GB800354A
Cited
GB847084A
Cited
GB840914A
Cited
US3164955A
Cited
US3170281A
Cited
US3103885A
Cited
US3177656A
Cited
US3202381A
Cited
US3173247A
Cited
US3119238A
Cited
GB1046909A
Cited
US3263414A
Cited
US3242811A
Cited
US3377801A
Cited
US3372546A
Cited
US3392864A
Cited
GB1089055A
Cited
US3525223A
Cited
GB1242231A
Cited
US3925133A
Cited
US3900675A
Cited
US3924034A
Cited
US3900668A
Cited
US3955784A
Cited
US3991248A
Cited
US3945203A
Cited
US4029844A
Cited
US3966855A
Cited
US3871179A
Cited
US3979005A
Cited
US4105819A
Cited
US4070993A
Cited
US4193828A
Cited
US4397901A
Cited
US4599256A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1992-06-26 | 1992-12-26 | 1993-06-27 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1996-06-26 | 1996-12-26 | 1997-06-27 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2000-06-26 | 2000-12-26 | 2001-06-27 | $7700.00 | Window Closed / Lapsed |