Abstract: A blade outer air seal is provided with a plurality of distinct cooling circuit schemes. Preferably, compact heat exchanger structures are utilized, and can be individually tailored to the particular location along the blade outer air seal. As an example, a greater pressure ratio exists between the products of combustion and the cooling air at the trailing edge than would be found at the leading edge. The present invention takes advantage of this distinction by utilizing cooling schemes that have a greater pressure drop at the trailing edge than the cooling schemes utilized closer to the leading edge.

Abstract: A turbine shroud section includes a cooling passage that bleeds cooling air through an opening in a surface. The cooling passage forms an angle relative to an expected fluid flow direction. The angle defines an angular component in a circumferential direction, which is aligned with the expected fluid flow direction to reduce momentum energy loss of fluid flow through the engine.

Abstract: A blade outer air seal is provided with a plurality of distinct cooling circuit schemes. Preferably, compact heat exchanger structures are utilized, and can be individually tailored to the particular location along the blade outer air seal. As an example, a greater pressure ratio exists between the products of combustion and the cooling air at the trailing edge than would be found at the leading edge. The present invention takes advantage of this distinction by utilizing cooling schemes that have a greater pressure drop at the trailing edge than the cooling schemes utilized closer to the leading edge.

Abstract: A compact heat exchanger for providing coolant gas flow through a part is provided. The compact heat exchanger reduces internal pressure losses through the compact heat exchanger. The compact heat exchanger has at least one inlet through which a coolant gas may enter, a circuit channel in fluid communication with the at least one inlet, and at least one outlet in fluid communication with the circuit channel through which the coolant gas may exit the circuit channel. The circuit channel is formed from superimposition of a plurality of alternating serpentine circuits, where at least one crossover of the circuit channel has a flow stabilizer that is formed in the channel and reduces internal pressure losses in the circuit channel.

Abstract: A turbine shroud section includes a cooling passage that bleeds cooling air through an opening in a surface. The cooling passage forms an angle relative to an expected fluid flow direction. The angle defines an angular component in a circumferential direction, which is aligned with the expected fluid flow direction to reduce momentum energy loss of fluid flow through the engine.