초록 ▼

A supplemental air cooling system for use in gas turbine engines to inhibit the ingestion of hot flow path gases into circumferential locations of turbine disk cavities is provided. The supplemental air cooling is provided through a simple set of cooling air holes located on each side of the turbine

A supplemental air cooling system for use in gas turbine engines to inhibit the ingestion of hot flow path gases into circumferential locations of turbine disk cavities is provided. The supplemental air cooling is provided through a simple set of cooling air holes located on each side of the turbine nozzle airfoil trailing edges, and proximately placed to be below the turbine nozzle structural element flow discouragers. Turbine disk cavity cooling purge air entering the disk cavity through the cooling air holes produces dynamic pressure cooling air jets which force the incoming hot ingestion air to turn circumferentially and go back out in the flow path before it enters the turbine disk cavity. The result is a decrease in hot gas ingestion, a reduction in disk rotor and static structural metal temperatures, a reduction in the amount of required cooling air flow, and enhanced performance of the gas turbine engine by virtue of improved specific fuel consumption.

대표청구항 ▼

1. A supplemental air cooling system, for use in gas turbine engines having hot gas flow discouraging structural elements, to inhibit ingestion of hot gas flow into certain circumferential locations of turbine disk cavities, said air cooling system comprising:a plurality of ingestion inhibiting dyna

1. A supplemental air cooling system, for use in gas turbine engines having hot gas flow discouraging structural elements, to inhibit ingestion of hot gas flow into certain circumferential locations of turbine disk cavities, said air cooling system comprising:a plurality of ingestion inhibiting dynamic jet orifices located on an underside of turbine nozzle trailing edges; said orifices penetrating through turbine nozzle hot gas flow path discouraging structural elements; said orifices being optionally located on each side of each stator blade airfoil trailing edge, or directly underneath each stator blade airfoil trailing edge; the centerline of each said orifices directed to a point within the turbine disk flow discourager cavity; said point being located about midway between the stationary turbine nozzle and the rotating turbine blade hot flow path gas discouraging structural elements; a flow of gas turbine engine cooling air traversing through said plurality of ingestion inhibiting dynamic jet orifices and flowing into the turbine disk flow discourager cavity; whereby the dynamic pressure of cooling air traversing through the plurality of ingestion inhibiting dynamic jet orifices and into the turbine disk flow discourager cavity, forces incoming hot flow gases to turn circumferentially and go back out into the path of hot gas flow before it can cause an adverse increase in internal component temperatures.