Control system for a turbine engine

Claim 2

A control system for a turbine engine including a compressor, a combustion chamber, a turbine and electrically actuated means for supplying fuel to said combustion chamber, comprising a probe disposable in a selected region of said engine including the combustion chamber outlet and the turbine inlet, said probe comprising a body having a first fluid passageway for receiving therethrough a gas sample from said selected region, said body having a second fluid passageway for conducting a coolant therethrough disposed in heat transfer relation to said gas sample flowing through said first fluid passageway, said passageways having means for providing a fixed flow rate ratio, and means for thermally insulating coolant flowing in said second fluid passageway from said selected region, means operatively connected to said probe for supplying coolant to said second fluid passageway, and an electrical supply circuit operatively connected to said electrically actuated means for supplying fuel to said combustion chamber, including means responsive to the temperature rise in said second fluid passageway of said probe body for correspondingly varying the voltage supplied to said electrically actuated means, thereby regulating the supply of fuel to said combustion chamber.

Claim 3

A control system for a turbine engine including a compressor, a combustion chamber, a turbine and electrically actuated means for supplying fuel to said combustion chamber according to claim 1, wherein said electrical supply circuit includes means for selectively varying the input signal for said electrically actuated means.

Claim 4

A control system for a turbine engine including a compressor, a combustion chamber, a turbine and electrically actuated means for supplying fuel to said combustion chamber according to claim 1, wherein said means operatively connected to said probe for supplying coolant to said second fluid passageway of said probe body is provided with an inlet disposed in a selected region of said engine including the inlet and outlet of said compressor for receiving gas under pressure as a coolant to be circulated through said second fluid passageway of said probe body.

Claim 5

A conTrol system for a turbine engine including a compressor, a combustion chamber, a turbine and electrically actuated means for supplying fuel to said combustion chamber according to claim 1, wherein said means operatively connected to said probe for supplying coolant to said second fluid passageway of said probe body consists of a closed fluid circuit including a pump.

Claim 6

A control system for a turbine engine including a compressor, a combustion chamber, a turbine and electrically actuated means for supplying fuel to said combustion chamber according to claim 1, wherein said means responsive to the temperature rise in said second fluid passageway of said probe body comprises thermocouples disposed in the inlet and outlet of said second fluid passageway of said probe body.

Claim 7

A control system for a turbine engine including a compressor, a combustion chamber, a turbine and electrically actuated means for supplying fuel to said combustion chamber according to claim 1, wherein said means for providing a fixed flow rate ratio in said fluid passageways comprises orifices.

Claim 8

A control system for a turbine engine including a compressor, a combustion chamber, a turbine and electrically actuated means for supplying fuel to said combustion chamber, according to claim 1, wherein said first fluid passageway of said probe body is elongated, having a gas inlet at one end thereof, said second fluid passageway of said probe body is annular and encompasses said first fluid passageway thereof.

Claim 9

A control system for a turbine engine including a compressor, a combustion chamber, a turbine and electrically actuated means for supplying fuel to said combustion chamber, comprising a probe disposable in a selected region of said engine including the combustion chamber outlet and the turbine inlet, said probe comprising a body having a first fluid passageway for receiving therethrough a gas sample from said selected region, said body having a second fluid passageway for conducting a coolant therethrough in heat transfer relation to said gas sample flowing through said first fluid passageway, said body having a distinct third fluid passageway disposed between said second fluid passageway and said selected region for thermally insulating coolant flowing in said second fluid passageway from said selected region, said second and third fluid passageways being noncommunicable, said passageways having means for providing a fixed flow rate ratio therein, first means operatively connected to said probe for supplying coolant to said second fluid passageway of said probe body, second means operatively connected to said probe for supplying coolant to said third fluid passageway of said probe body, and an electrical supply circuit operatively connected to said electrically actuated means for supplying fuel to said combustion chamber, including means responsive to the temperature rise in said second fluid passageway of said probe body for correspondingly varying the voltage supplied to said electrically actuated means thereby regulating the supply of fuel to said combustion chamber.

Claim 10

A control system for a turbine engine including a compressor, a combustion chamber, a turbine and electrically actuated means for supplying fuel to said combustion chamber, comprising a probe disposable in a selected region of said engine including the combustion chamber outlet and the turbine inlet, said probe comprising a body having a first fluid passageway for receiving therethrough a gas sample from said selected region, said body having a second fluid passageway for conducting a coolant therethrough in heat transfer relation to said gas sample flowing through said first fluid passageway, said body having a distinct third fluid passageway disposed between said second fluid passageway and said selected region for thermally insulating coolant flowing in said second fluid passageway from said selected region, said second and third fluid passageways being noncommunicable, said passageways having means for providing a fixed flow rate ratio therein, first means operatively connected to said probe for supplying coolant to said second fluid passageway of said probe body, second means operatively connected to said probe for supplying coolant to said third fluid passageway of said probe body, and an electrical supply circuit operatively connected to said electrically actuated means for supplying fuel to said combustion chamber, including means responsive to the temperature rise in said second fluid passageway of said probe body for correspondingly varying the voltage supplied to said electrically actuated means thereby regulating the supply of fuel to said combustion chamber.

Claim 11

A control system for a turbine engine including a compressor, a combustion chamber, a turbine and electrically actuated means for supplying fuel to said combustion chamber according to claim 8, when said electrical supply circuit includes means for selectively varying the input signal for said electrically actuated means.

Claim 12

A control system for a turbine engine including a compressor, a combustion chamber, a turbine and electrically actuated means for supplying fuel to said combustion chamber according to claim 8, when said means operatively connected to said probe for supplying coolant to said second and third fluid passageways of said probe body are provided with inlets disposed in a selected region of said engine including the inlet and outlet of said compressor for receiving gas under pressure as a coolant to be circulated through said second and third fluid passageways of said probe body.

Claim 13

A control system foR a turbine engine including a compressor, a combustion chamber, a turbine and electrically actuated means for supplying fuel to said combustion chamber according to claim 8, wherein said means operatively connected to said probe for supplying coolant to said second and third fluid passageways of said probe body consist of a closed fluid circuit including a pump.

Claim 14

A control system for a turbine engine including a compressor, a combustion chamber, a turbine and electrically actuated means for supplying fuel to said combustion chamber according to claim 8, wherein said means responsive to the temperature rise in said second fluid passageway of said probe body comprises thermocouples disposed in the inlet and outlet of said second fluid passageway of said probe body.

Claim 15

A control system for a turbine engine including a compressor, a combustion chamber, a turbine and electrically actuated means for supplying fuel to said combustion chamber according to claim 8, wherein said means for providing a fixed flow rate ratio in said fluid passageways comprises orifices.

Claim 16

A control system for a turbine engine including a compressor, a combustion chamber, a turbine and electrically actuated means for supplying fuel to said combustion chamber, according to claim 8, wherein said first fluid passageway of said probe body is elongated, having a gas inlet at one end thereof, said second fluid passageway of said probe body is annular and encompasses said first fluid passageway thereof, and said third fluid passageway of said probe body is annular and encompasses said second fluid passageway in spaced relation.