| タイトル | Northrop Grumman TR202 LOX/GH2 Deep Throttling Pintle Injector Performance, Stability, and Heat Transfer Measurements |
| 著者（英） | Foote, J. P.; Wall, T. R.; Gromski, J. M.; Majamaki, A. N.; Chianese, S. G.; Weinstock, V. D.; Litchford, R. J. |
| 著者所属（英） | NASA Marshall Space Flight Center |
| 発行日 | 2010-05-03 |
| 言語 | eng |
| 内容記述 | Engineers from Northrop Grumman and NASA MSFC are teaming to develop deep throttling technologies for future crewed lunar descent engines for NASA s Propulsion and Cryogenic Advanced Development (PCAD) program. A complete TR202 conceptual engine design has been completed. Pintle injector technology development is the current project focus because injector operation relates to many of the overall engine technology challenges, and injector characteristics contribute significantly to combustion chamber and overall cycle design. In order to maximize injector and engine capability provided to lunar mission and vehicle designers, it is important to understand injector performance, stability, and heat transfer characteristics across a large throttle range and over a range of mixture ratios. The mixing and vaporization effectiveness of an injector can be characterized by C* efficiency and energy release efficiency (ERE). Heat transfer characteristics of the injector can be studied using calorimetry chamber hardware. The primary objectives of this test program were: a) Achieve >98 C*% efficiency at high throttle settings (.75% power). b) Avoid low frequency and high frequency instability over a 10:1 throttle range with a high performing injector. c) Measure heat flow to combustion chamber walls, and determine if there is enough heat flow to close a deep throttling expander engine cycle balance, while maintaining reasonable combustion chamber wall temperatures. The TR202 test-bed pintle injector was designed and built for flexibility and operability on the test stand, with a DOE testing approach. Heavy-weight hardware was used for structural margin, though flow passages were flight-like. Throttling of the LOX flow area was achieved by the use of shims that controlled how far the pintle injector LOX slots protruded into the combustion chamber. TR202 test-bed pintle injector testing was conducted at NASA MSFC s test stand 116 and NASA MSFC combustion chamber calorimetry hardware was used. All primary test objectives were met during this test campaign. Detailed test results and conclusions will be provided in the complete paper and presentation. |
| NASA分類 | Spacecraft Propulsion and Power |
| レポートNO | M10-0323 |
| 権利 | Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/271399 |
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