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  • 1
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    Preliminary flight evaluation of an engine performance optimization algorithm (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A performance-seeking control (PSC) algorithm has undergone initial flight test evaluation in subsonic operation of a PW 1128-engined F-15; this algorithm is designed to optimize the quasi-steady performance of an engine for three primary modes: (1) minimum fuel consumption, (2) minimum fan-turbine inlet temperature (FTIT), and (3) maximum thrust. The flight test results have verified a thrust-specific fuel consumption reduction of 1 percent, up to 100 R decreases in FTIT, and increases of as much as 12 percent in maximum thrust. PSC technology promises to be of value in next-generation tactical and transport aircraft.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 91-1998
    Format: text
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 2
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    A simulation study of turbofan engine deterioration estimation using Kalman filtering techniques (1991)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: 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.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-104233 , H-1616 , NAS 1.15:104233
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    A preliminary evaluation of an F100 engine parameter estimation process using flight data (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The parameter estimation algorithm developed for the F100 engine is described. The algorithm is a two-step process. The first step consists of a Kalman filter estimation of five deterioration parameters, which model the off-nominal behavior of the engine during flight. The second step is based on a simplified steady-state model of the 'compact engine model' (CEM). In this step the control vector in the CEM is augmented by the deterioration parameters estimated in the first step. The results of an evaluation made using flight data from the F-15 aircraft are presented, indicating that the algorithm can provide reasonable estimates of engine variables for an advanced propulsion-control-law development.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 90-1921
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Preliminary flight evaluation of an engine performance optimization algorithm (1991)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A performance seeking control (PSC) algorithm has undergone initial flight test evaluation in subsonic operation of a PW 1128 engined F-15. This algorithm is designed to optimize the quasi-steady performance of an engine for three primary modes: (1) minimum fuel consumption; (2) minimum fan turbine inlet temperature (FTIT); and (3) maximum thrust. The flight test results have verified a thrust specific fuel consumption reduction of 1 pct., up to 100 R decreases in FTIT, and increases of as much as 12 pct. in maximum thrust. PSC technology promises to be of value in next generation tactical and transport aircraft.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-4328 , H-1745 , NAS 1.15:4328 , Joint Propulsion Conference; Jun 24, 1991 - Jun 26, 1991; Sacramento, CA; United States
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
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