Raytheon Technologies Corporation

United Technologies Corporation

Rtx Corporation

Renee J Behlman

Tracy A Propheter-Hinckley

Matthew A Devore

Raymond C Surace

Barry M Ford

James Glaspey

Matthew A Turner

A flowpath component for a gas turbine engine includes a body having a leading edge and a trailing edge. A first exterior wall connects the leading edge to the trailing edge and a second exterior wall connects the leading edge to the trailing edge. At least one first internal cooling passage has a first inlet at a first end of the body. At least one second internal cooling passage has a second inlet at a second end of the body. The at least one first internal cooling passage is isolated from the at least one second internal cooling passage.

Multi-flow cooling circuit for gas turbine engine flowpath component

A turbine engine component includes a wall extending from a leading edge to a trailing edge. The wall includes a hot side facing a gaspath when the gaspath component is in an installed state, and a cold side opposite the hot side. At least one minicore cooling circuit is disposed between the hot side and the cold side within the wall. At least one cooling fluid inlet connects the minicore cooling circuit to a coolant source. At least one film cooling hole connects the minicore cooling circuit to the hot side surface. The minicore cooling circuit includes an edge plenum having a thickness normal to the hot side surface that is larger than a thickness of the majority of the minicore cooling circuit normal to the hot side surface. The edge plenum is a portion of the at least one minicore cooling circuit most proximate to one of the leading edge and the trailing edge.

Gaspath component including minicore plenums

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Colchester, CT, United States of America

Renee J Behlman