초록 ▼

A pressurized gas turbine engine is disclosed which utilizes a new turbine design. Pressurized gas is supplied by nozzle gas ways in the turbine to gas nozzles affixed to the perimeter of the turbine. The gas nozzles may be recessed in the turbine perimeter or extend from the turbine perimeter. The

A pressurized gas turbine engine is disclosed which utilizes a new turbine design. Pressurized gas is supplied by nozzle gas ways in the turbine to gas nozzles affixed to the perimeter of the turbine. The gas nozzles may be recessed in the turbine perimeter or extend from the turbine perimeter. The gas nozzles may be equipped with gas exit cones to enhance the efficiency of the nozzles. The axis of the nozzles have an oblique angle with the direction of rotation of the turbine. Pressurized gas is supplied to the nozzle gas ways through one or more shaft gas ways in the turbine shaft, or is supplied through engine gas ports in the front wall of the turbine engine to gas supply zones which are hydraulically separated by seal rings on the front face of the turbine, each gas supply zone being hydraulically connected to one or more nozzle gas ways.

대표청구항 ▼

A pressurized gas turbine engine is disclosed which utilizes a new turbine design. Pressurized gas is supplied by nozzle gas ways in the turbine to gas nozzles affixed to the perimeter of the turbine. The gas nozzles may be recessed in the turbine perimeter or extend from the turbine perimeter. The

A pressurized gas turbine engine is disclosed which utilizes a new turbine design. Pressurized gas is supplied by nozzle gas ways in the turbine to gas nozzles affixed to the perimeter of the turbine. The gas nozzles may be recessed in the turbine perimeter or extend from the turbine perimeter. The gas nozzles may be equipped with gas exit cones to enhance the efficiency of the nozzles. The axis of the nozzles have an oblique angle with the direction of rotation of the turbine. Pressurized gas is supplied to the nozzle gas ways through one or more shaft gas ways in the turbine shaft, or is supplied through engine gas ports in the front wall of the turbine engine to gas supply zones which are hydraulically separated by seal rings on the front face of the turbine, each gas supply zone being hydraulically connected to one or more nozzle gas ways. er surfaces of the blades during rotation of the blades from the maximum pitch to the minimum pitch is spherically-shaped. The inner surfaces of the blades substantially conform to the spherical outer surface portion of the hub, thereby reducing inner gaps formed therebetween. At least one of the blades includes a seal attached to the inner surface of the at least one of the blades. The seal is effectively in contact with the spherical outer surface portion of the hub as the blades are rotated about their axis, thereby further reducing the inner gaps. The turbine installation also includes an electrical closed-loop control system including a processor and sensors. The control system adjusts the pitch of the blades in response to electrical signals from the sensors.