Stechman et al., 1969 - Google Patents
Design criteria for film cooling for small liquid-propellant rocket engines.Stechman et al., 1969
- Document ID
- 8649037830233060750
- Author
- Stechman R
- Oberstone J
- Stechman J
- Publication year
- Publication venue
- Journal of Spacecraft and Rockets
External Links
Snippet
THERE is a strong interest in the application of advanced propellant combinations to small rocket engines. Most of the advanced propellant technology gathered to date has been with engines in the 1000-to 100,000-lb-thrust level. Until recently, little was known about the …
- 239000003380 propellant 0 title abstract description 34
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING ENGINES OR PUMPS
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket- engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket- engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details
- F02K9/62—Combustion or thrust chambers
- F02K9/64—Combustion or thrust chambers having cooling arrangements
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING ENGINES OR PUMPS
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket- engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket- engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/56—Control
- F02K9/58—Propellant feed valves
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING ENGINES OR PUMPS
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket- engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket- engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/46—Feeding propellants using pumps
- F02K9/48—Feeding propellants using pumps driven by a gas turbine fed by propellant combustion gases or fed by vaporized propellants or other gases
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING ENGINES OR PUMPS
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket- engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket- engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/425—Rocket- engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants propellants
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING ENGINES OR PUMPS
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket- engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/97—Rocket nozzles
- F02K9/974—Nozzle- linings; Ablative coatings
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Stechman et al. | Design criteria for film cooling for small liquid-propellant rocket engines. | |
| Karabeyoglu et al. | Combustion of liquefying hybrid propellants: Part 2, stability of liquid films | |
| US6880326B2 (en) | High regression rate hybrid rocket propellants and method of selecting | |
| Betti et al. | Chemical reaction effects on heat loads of CH4/O2 and H2/O2 rockets | |
| Evans et al. | Performance of a solid-fuel ramjet combustor with bypass air addition | |
| Paccagnella et al. | Testing of a long-burning-time paraffin-based hybrid rocket motor | |
| Kirchberger | Investigation on heat transfer in small hydrocarbon rocket combustion chambers | |
| Vasques et al. | Effect of pintle injector element geometry on combustion in a liquid oxygen/liquid methane rocket engine | |
| Schneider et al. | Active control of dual-bell nozzle operation mode transition by film cooling and mixture ratio variation | |
| Wooldridge et al. | Internal ballistic considerations in hybrid rocket design. | |
| Sopok et al. | Unified computer model for predicting thermochemical erosion in gun barrels | |
| Shih-Sin et al. | A review of recent developments in hybrid rocket propulsion and its applications | |
| COULBERT | Selecting cooling techniques for liquid rockets for spacecraft | |
| RAPP | High energy-density liquid rocket fuel performance | |
| Dunn et al. | Nozzle performance predictions using the TDK 97 code | |
| Kara et al. | Propulsion system design for mars ascent vehicles by using the in-situ CO2 | |
| Bruno | Chemical microthrusters-Effect of scaling on combustion | |
| Bulman et al. | Simulated LOX-augmented nuclear thermal rocket (LANTR) testing | |
| Browne | Modeling ablative and regenerative cooling systems for an ethylene ethane nitrous oxide liquid fuel rocket engine | |
| Sohn | A Unified Theory of Ammonium Perehlorate Deflagration and the Low Pressure Deflagration Limit | |
| Linne et al. | Chemical propulsion: Greater than 60 years of leadership and innovation at nasa glenn research center | |
| HOWELL | Film cooling design criteria for small rocket engines | |
| Kara et al. | Hybrid Propulsion System: Novel Propellant Design for Mars Ascent | |
| Linne | Carbon monoxide and oxygen combustion experiments: a demonstration of Mars in situ propellants | |
| Bartlett | A systematic method for determination of ablation rates in a corrosive environment |