Turbine inlet temperature computer

Claim 2

A turbine inlet temperature computer for computing the turbine inlet temperature of a gas turbine-type engine having at least a compressor stage, a burner stage and a turbine stage on the basis of the compressor discharge pressure, the turbine exit pressure, the mass fuel flow and the burner inlet temperature comprising: means for producing a compressor discharge pressure direct current potential signal of a magnitude proportional to the discharge pressure of said compressor stage, means for producing a turbine exit pressure direct current potential signal of a magnitude proportional to the exit pressure of said turbine stage, means responsive to said compressor discharge pressure signal and said turbine exit pressure signal for producing a turbine expansion ratio direct current potential output signal of a magnitude proportional to the expansion ratio of said turbine stage, means responsive to said turbine expansion ratio signal for producing a direct current potential signal which is the reciprocal of said turbine K factor, means for producing a mass fuel flow direct current potential signal of a magnitude proportional to the mass fuel flow to said turbine engine, means for producing a burner inlet temperature direct current potential signal of a magnitude proportional to the inlet temperature of said burner stage, means for dividing Said mass fuel flow signal by said compressor discharge pressure signal, means for multiplying the quotient of said mass fuel flow signal divided by said compressor discharge pressure signal by said reciprocal of said turbine K factor signal, and means for adding said burner inlet temperature signal to the product of the quotient of said mass fuel flow signal divided by said compressor discharge pressure signal multiplied by said reciprocal of said turbine K factor signal.

Claim 3

A turbine inlet temperature computer for computing the turbine inlet temperature of a gas turbine-type engine having at least a compressor stage, a burner stage and a turbine stage on the basis of the compressor discharge pressure, the turbine exit pressure, the mass fuel flow and the burner inlet temperature comprising: means for producing a compressor discharge pressure direct current potential signal of a magnitude proportional to the discharge pressure of said compressor stage, means for producing a turbine exit pressure direct current potential signal of a magnitude proportional to the exit pressure of said turbine stage, means for dividing said compressor discharge pressure signal by said turbine exit pressure signal for producing a turbine expansion ratio direct current potential output signal of a magnitude proportional to the expansion ratio of said turbine stage, means responsive to said turbine expansion ratio signal for producing a direct current potential signal which is the reciprocal of said turbine K factor, means for producing a mass fuel flow direct current potential signal of a magnitude proportional to the mass fuel flow to said turbine engine, means for producing a burner inlet temperature direct current potential signal of a magnitude proportional to the inlet temperature of said burner stage, means for dividing said mass fuel flow signal by said compressor discharge pressure signal, means for multiplying the quotient of said mass fuel flow signal divided by said compressor discharge pressure signal by said reciprocal of said turbine K factor signal, and means for adding said burner inlet temperature signal to the product of the quotient of said mass fuel flow signal divided by said compressor discharge pressure signal multiplied by said reciprocal of said turbine K factor signal.

Claim 4

A turbine inlet temperature computer for computing the turbine inlet temperature of a gas turbine-type engine having at least a compressor stage, a burner stage and a turbine stage on the basis of the compressor discharge pressure, the turbine exit pressure, the mass fuel flow and the burner inlet temperature comprising: means for producing a compressor discharge pressure direct current potential signal of a magnitude proportional to the discharge pressure of said compressor stage, means for producing a turbine exit pressure direct current potential signal of a magnitude proportional to the exit pressure of said turbine stage, means for dividing said compressor discharge pressure signal by said turbine exit pressure signal for producing a turbine expansion ratio direct current potential output signal of a magnitude proportional to the expansion ratio of said turbine stage, means responsive to said turbine expansion ratio signal for producing a direct current potential signal which is the reciprocal of said turbine K factor, means for producing a mass fuel flow direct current potential signal of a magnitude proportional to the mass fuel flow to said turbine engine, means for producing a burner inlet temperature direct current potential signal of a magnitude proportional to the inlet temperature of said burner stage, means for dividing said mass fuel flow signal by said compressor discharge pressure signal, means for multiplying the quotient of said mass fuel flow signal divided by said compressor discharge pressure signal by said reciprocal of said turbine K factor signal, and means for adding said burner inlet temperature signal to the product of the quotient of said mass fuel flow signal divided by said compressor discharge pressure signal multiplied by said reciprocal of said turbine K factor signal.

Claim 5

A turbine inlet temperature computer for computing the turbine inlet temperature of a gas turbine-type engine having at least a compressor stage, a burner state and a turbine stage on the basis of the compressor discharge pressure, the turbine exit pressure, the mass fuel flow and the burner inlet temperature comprising: means for producing a compressor discharge pressure direct current potential signal of a magnitude proportional to the discharge pressure of said compressor stage, means for producing a turbine exit pressure direct current potential signal of a magnitude proportional to the exit pressure of said turbine stage, means responsive to said compressor discharge pressure signal and said turbine exit pressure signal for producing a turbine expansion ratio direct current potential output signal of a magnitude proportional to the expansion ratio of said turbine stage, means responsive to said turbine stage, means responsive to said turbine expansion ratio signal for producing a direct current potential signal which is the reciprocal of said turbine K factor, means for producing a mass fuel flow direct current potential signal of a magnitude proportional to the mass fuel flow to said turbine engine, means for producing a burner inlet temperature direct current potential signal of a magnitude proportional to the inlet temperature of said burner stage, a divider-multiplier circuit of the type capable of dividing the dividend direct current potential signal by a divisor direct current potential signal and multiplying the quotient by a multiplier direct current potential signal having at least a respective input circuit for each the dividend, divisor and multiplier electric signals and a dIrect current potential summing input circuit for producing the turbine inlet temperature direct current potential output signal which is the quotient of said mass fuel flow signal divided by said compressor discharge pressure signal multiplied by said reciprocal of said turbine K factor signal plus said burner inlet temperature signal, means for applying said mass fuel flow signal to said dividend input circuit of said second divider-multiplier circuit, means for applying said compressor discharge pressure signal to said divisor input circuit of said second divider-multiplier circuit, means for applying said reciprocal of said turbine K factor signal to said multiplier input circuit of said second divider-multiplier circuit, and means for applying said burner inlet temperature signal to said summing input circuit of said second divider-multiplier circuit.

Claim 6

A turbine inlet temperature computer for computing the turbine inlet temperature of a gas turbine-type engine having at least a compressor stage, a burner state and a turbine stage on the basis of the compressor discharge pressure, the turbine exit pressure, the mass fuel flow and the burner inlet temperature comprising: means for producing a compressor discharge pressure direct current potential signal of a magnitude proportional to the discharge pressure of said compressor stage, means for producing a turbine exit pressure direct current potential signal of a magnitude proportional to the exit pressure of said turbine stage, means responsive to said compressor discharge pressure signal and said turbine exit pressure signal for producing a turbine expansion ratio direct current potential output signal of a magnitude proportional to the expansion ratio of said turbine stage, means responsive to said turbine stage, means responsive to said turbine expansion ratio signal for producing a direct current potential signal which is the reciprocal of said turbine K factor, means for producing a mass fuel flow direct current potential signal of a magnitude proportional to the mass fuel flow to said turbine engine, means for producing a burner inlet temperature direct current potential signal of a magnitude proportional to the inlet temperature of said burner stage, a divider-multiplier circuit of the type capable of dividing the dividend direct current potential signal by a divisor direct current potential signal and multiplying the quotient by a multiplier direct current potential signal having at least a respective input circuit for each the dividend, divisor and multiplier electric signals and a dIrect current potential summing input circuit for producing the turbine inlet temperature direct current potential output signal which is the quotient of said mass fuel flow signal divided by said compressor discharge pressure signal multiplied by said reciprocal of said turbine K factor signal plus said burner inlet temperature signal, means for applying said mass fuel flow signal to said dividend input circuit of said second divider-multiplier circuit, means for applying said compressor discharge pressure signal to said divisor input circuit of said second divider-multiplier circuit, means for applying said reciprocal of said turbine K factor signal to said multiplier input circuit of said second divider-multiplier circuit, and means for applying said burner inlet temperature signal to said summing input circuit of said second divider-multiplier circuit.

Claim 7

A turbine inlet temperature computer for computing the turbine inlet temperature of a gas turbine-type engine having at least a compressor stage, a burner stage and a turbine stage on the basis of the compressor discharge pressure, the turbine exit pressure, the mass fuel flow and the burner inlet temperature comprising: means for producing a compressor discharge pressure direct current potential signal of a magnitude proportional to the discharge pressure of said compressor stage, means for producing a turbine exit pressure direct current potential signal of a magnitude proportional to the exit pressure of said turbine stage, means for producing a constant direct current potential signal of a selected magnitude, a first divider-multiplier circuit of the type capable of dividing a dividend direct current potential signal by a divisor direct current potential signal and multiplying the quotient by a multiplier direct current potential signal having at least a respective input circuit for each the dividend, divisor and multiplier input signals for producing a turbine expansion ratio direct current potential output signal of a magnitude proportional to the expansion ratio of said turbine stage, means for applying said compressor discharge pressure signal to said dividend input circuit of said first divider-multiplier circuit, means for applying said turbine exit pressure signal to said divisor input circuit of said first divider-multiplier circuit, means for applying said constant direct current potential signal to said multiplier input circuit of said first divider-multiplier circuit, a curve generator responsive to said turbine expansion ratio signal for producing a direct current potential output signal which is the reciprocal of the turbine K factor, means for applying said turbine expansion ratio output signal from said first divider-multiplier circuit to said curve generator, means for producing a mass fuel flow direct current potential signal of a magnitude proportional to the weight of fuel flow to said turbine engine, means for producing a burner inlet temperature direct current potential signal of a magnitude proportional to the inlet temperature of said burner stage, a second divider-multiplier circuit of the type capable of dividing a dividend direct current potential signal by a divisor direct current potential signal and multiplying the quotient by a multiplier direct current potential signal having at least a respective input circuit for each the dividend, divisor and multiplier input signals and a direct current potential signal summing input circuit for producing the turbine inlet temperature direct current potential output signal which is the quotient of said mass fuel flow signal divided by said compressor discharge pressure signal multiplied by the reciprocal of said turbine K factor signal plus said burner inlet temperature signal, means for applying said mass fuel flow signal to said dividend input circuit of said second divider-multiplier circuit, means for applying said compressor discharge pressure signal to said divisor input circuit of said second divider-multiplier circuit, means for Applying said curve generator output signal to said multiplier input circuit of said second divider-multiplier circuit, and means for applying said burner inlet temperature signal to said summing input circuit of said second divider-multiplier circuit.

Claim 8

A turbine inlet temperature computer for computing the turbine inlet temperature of a gas turbine-type engine having at least a compressor stage, a burner stage and a turbine stage on the basis of the compressor discharge pressure, the turbine exit pressure, the mass fuel flow and the burner inlet temperature comprising: means for producing a compressor discharge pressure direct current potential signal of a magnitude proportional to the discharge pressure of said compressor stage, means for producing a turbine exit pressure direct current potential signal of a magnitude proportional to the exit pressure of said turbine stage, means for producing a constant direct current potential signal of a selected magnitude, a first divider-multiplier circuit of the type capable of dividing a dividend direct current potential signal by a divisor direct current potential signal and multiplying the quotient by a multiplier direct current potential signal having at least a respective input circuit for each the dividend, divisor and multiplier input signals for producing a turbine expansion ratio direct current potential output signal of a magnitude proportional to the expansion ratio of said turbine stage, means for applying said compressor discharge pressure signal to said dividend input circuit of said first divider-multiplier circuit, means for applying said turbine exit pressure signal to said divisor input circuit of said first divider-multiplier circuit, means for applying said constant direct current potential signal to said multiplier input circuit of said first divider-multiplier circuit, a curve generator responsive to said turbine expansion ratio signal for producing a direct current potential output signal which is the reciprocal of the turbine K factor, means for applying said turbine expansion ratio output signal from said first divider-multiplier circuit to said curve generator, means for producing a mass fuel flow direct current potential signal of a magnitude proportional to the weight of fuel flow to said turbine engine, means for producing a burner inlet temperature direct current potential signal of a magnitude proportional to the inlet temperature of said burner stage, a second divider-multiplier circuit of the type capable of dividing a dividend direct current potential signal by a divisor direct current potential signal and multiplying the quotient by a multiplier direct current potential signal having at least a respective input circuit for each the dividend, divisor and multiplier input signals and a direct current potential signal summing input circuit for producing the turbine inlet temperature direct current potential output signal which is the quotient of said mass fuel flow signal divided by said compressor discharge pressure signal multiplied by the reciprocal of said turbine K factor signal plus said burner inlet temperature signal, means for applying said mass fuel flow signal to said dividend input circuit of said second divider-multiplier circuit, means for applying said compressor discharge pressure signal to said divisor input circuit of said second divider-multiplier circuit, means for Applying said curve generator output signal to said multiplier input circuit of said second divider-multiplier circuit, and means for applying said burner inlet temperature signal to said summing input circuit of said second divider-multiplier circuit.