| タイトル | A simulation study of turbofan engine deterioration estimation using Kalman filtering techniques |
| 本文（外部サイト） | http://hdl.handle.net/2060/19910015833 |
| 著者（英） | Lambert, Heather H. |
| 著者所属（英） | NASA Dryden Flight Research Facility |
| 発行日 | 1991-06-01 |
| 言語 | eng |
| 内容記述 | Deterioration of engine components may cause off-normal engine operation. The result is an unecessary loss of performance, because the fixed schedules are designed to accommodate a wide range of engine health. These fixed control schedules may not be optimal for a deteriorated engine. This problem may be solved by including a measure of deterioration in determining the control variables. These engine deterioration parameters usually cannot be measured directly but can be estimated. A Kalman filter design is presented for estimating two performance parameters that account for engine deterioration: high and low pressure turbine delta efficiencies. The delta efficiency parameters model variations of the high and low pressure turbine efficiencies from nominal values. The filter has a design condition of Mach 0.90, 30,000 ft altitude, and 47 deg power level angle (PLA). It was evaluated using a nonlinear simulation of the F100 engine model derivative (EMD) engine, at the design Mach number and altitude over a PLA range of 43 to 55 deg. It was found that known high pressure turbine delta efficiencies of -2.5 percent and low pressure turbine delta efficiencies of -1.0 percent can be estimated with an accuracy of + or - 0.25 percent efficiency with a Kalman filter. If both the high and low pressure turbine are deteriorated, the delta efficiencies of -2.5 percent to both turbines can be estimated with the same accuracy. |
| NASA分類 | AIRCRAFT PROPULSION AND POWER |
| レポートNO | 91N25147
NAS 1.15:104233
H-1616
NASA-TM-104233 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/132180 |
