| タイトル | Large Engine Technology Program. Task 21: Rich Burn Liner for Near Term Experimental Evaluations |
| 本文（外部サイト） | http://hdl.handle.net/2060/20050060999 |
| 著者（英） | Padget, F. C.; Siskind, K. S.; Hautman, D. J.; Kwoka, D.; Lohmann, R. P. |
| 著者所属（英） | United Technologies Research Center |
| 発行日 | 2005-01-01 |
| 言語 | eng |
| 内容記述 | The objective of the task reported herein, which was conducted as part of the NASA sponsored Large Engine Technology program, was to define and evaluate a near-term rich-zone liner construction based on currently available materials and fabrication processes for a Rich-Quench-Lean combustor. This liner must be capable of operation at the temperatures and pressures of simulated HSCT flight conditions but only needs sufficient durability for limited duration testing in combustor rigs and demonstrator engines in the near future. This must be achieved at realistic cooling airflow rates since the approach must not compromise the emissions, performance, and operability of the test combustors, relative to the product engine goals. The effort was initiated with an analytical screening of three different liner construction concepts. These included a full cylinder metallic liner and one with multiple segments of monolithic ceramic, both of which incorporated convective cooling on the external surface using combustor airflow that bypassed the rich zone. The third approach was a metallic platelet construction with internal convective cooling. These three metal liner/jacket combinations were tested in a modified version of an existing Rich-Quench-Lean combustor rig to obtain data for heat transfer model refinement and durability verification. |
| NASA分類 | Aircraft Design, Testing and Performance |
| レポートNO | NASA/CR-2005-213136
E-14650 |
| 権利 | No Copyright |
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