Power available indicator

Claim 3

The combination as set forth in claim 1, wherein said storage means includes a manually set potentiometer connected to a voltage source.

Claim 4

In a method for signaling in flight the maximum power available from a turbine engine where compressor inlet temperature and pressure and output shaft speed are continuously sensed, which comprises: a. manually storing engine performance parameters including turbine inlet temperature controlled for a particular reference condition; b. generating a shaft horsepower available signal for optimum operating shaft speed as a function of said sensed compressor inlet temperature and pressure and said reference data; c. generating a loss in shaft horsepower signal, resulting from operating at a shaft speed other than optimum operating speed, as a function of sensed data including said output shaft speed and said optimum shaft horsepower; d. combining said optimum shaft horsepower available and loss in shaft horsepower signals to obtain a signal representing said available shaft horsepower; and e. converting said available shaft horsepower signal into format for display to the pilot.

Claim 5

In a method for signaling in flight the maximum power available from a turbine engine where compressor inlet temperature and pressure and output shaft speed are continuously sensed, which comprises: a. manually storing engine performance parameters including turbine inlet temperature controlled for a particular reference condition; b. generating a shaft horsepower available signal for optimum operating shaft speed as a function of said sensed compressor inlet temperature and pressure and said reference data; c. generating a loss in shaft horsepower signal, resulting from operating at a shaft speed other than optimum operating speed, as a function of sensed data including said output shaft speed and said optimum shaft horsepower; d. combining said optimum shaft horsepower available and loss in shaft horsepower signals to obtain a signal representing said available shaft horsepower; and e. converting said available shaft horsepower signal into format for display to the pilot.

Claim 8

In a system for predicting the performance capabilities of an aircraft turbine engine under marginal power available conditions, the combination which comprises: a. a plurality of inflight sensors for measuring the engine compressor inlet temperature, the compressor inlet pressure and the output shaft speed of the engine; b. a means for storing reference quantities representative of engine performance reference data including a rated turbine inlet temperature; c. a generator for generating during flight from said sensed parameters and said reference quantities a signal representing said available power; and d. means for utilizing said available power signal, said generator including i. means for producing a shaft horsepower available signal at optimum operating shaft speed, said horsepower available signal being based on stored engine performance reference quantities including a rated turbine inlet temperature and engine compressor inlet temperature and pressure, ii. means for producing a loss in shaft horsepower signal corresponding to operation at other than optimum shaft speed, said loss in horsepower signal being based on engine performance reference quantities and the inflight sensed parameters, and iii. means for combining the optimum shaft horsepower available signal with the loss in horsepower signal to generate an available shaft horsepower signal.

Claim 9

In a system for predicting the performance capabilities of an aircraft turbine engine under marginal power available conditions, the combination which comprises: a. a plurality of inflight sensors for measuring the engine compressor inlet temperature, the compressor inlet pressure and the output shaft speed of the engine; b. a means for storing reference quantities representative of engine performance reference data including a rated turbine inlet temperature; c. a generator for generating during flight from said sensed parameters and said reference quantities a signal representing said available power; and d. means for utilizing said available power signal, said generator including i. means for producing a shaft horsepower available signal at optimum operating shaft speed, said horsepower available signal being based on stored engine performance reference quantities including a rated turbine inlet temperature and engine compressor inlet temperature and pressure, ii. means for producing a loss in shaft horsepower signal corresponding to operation at other than optimum shaft speed, said loss in horsepower signal being based on engine performance reference quantities and the inflight sensed parameters, and iii. means for combining the optimum shaft horsepower available signal with the loss in horsepower signal to generate an available shaft horsepower signal.

Claim 10

In an aircraft information system where a turbine inlet pressure and temperature and turbine output shaft speed are sensed to produce electrical signals proportional thereto, the combination comprising: a. means to store a constant electrical signal applicable to a given model of turbine and proportional to the specified controlled temperature at the turbine inlet; b. means to store electrical signals proportional to engine rated horsepower at sea level for said model operating in a particular engine operating mode; c. means to store signals proportional to standard temperature and pressure at sea level, and d. means to generate from said signals an output signal representative of power available from said turbine at the sensed temperature and pressure.

Claim 11

In an aircraft information system where a turbine inlet pressure and temperature and turbine output shaft speed are sensed to produce electrical signals proportional thereto, the combination comprising: a. means to store a constant electrical signal applicable to a given model of turbine and proportional to the specified controlled temperature at the turbine inlet; b. means to store electrical signals proportional to engine rated horsepower at sea level for said model operating in a particular engine operating mode; c. means to store signals proportional to standard temperature and pressure at sea level, and d. means to generate from said signals an output signal representative of power available from said turbine at the sensed temperature and pressure.