| description abstract | The work described in this paper utilizes dust ingestion experimental results obtained using three Pratt/Whitney F100, two GE F101, one Pratt/Whitney J57, and three Pratt/Whitney TF33 military engines and two different combustor rigs (one utilizing a sector of the Pratt/Whitney F100 annular combustor and the other utilizing an Allison T56 can combustor) to scale results so that these previous experiments can be used to approximate the response of more current aircraft engines to foreign particle ingestion. Modern engines experience a combination of compression system erosion and material deposition in the combustor and on the highpressure turbine (HPT) inlet vanes (and rotor blade complications) whereas the older engines (P/W TF33 and J57) experienced primarily an erosion problem as a result of the lower turbine inlet temperatures (TIT). As part of the results presented in this paper, the scaled estimates of material accumulation and component degradation have been compared to documented inflight ash encounters, specifically KLM Flight 867, British Airways Flight 009, Qantas Flight 370, and an NASA scientific research flight. The results of the study allow one to make estimates of the time to initial issues for the RR RB211, the GE CF6, the GE/Snecma CFM56, and the P/W JT9D engines encountering dust clouds of specific concentration. Current engine certification procedures do not require any specific test condition that would approach the engine issues described in this paper. | |
