THERMALLY ISOLATED TURBINE SECTION FOR A GAS TURBINE ENGINE

摘要

A gas turbine engine includes a turbine section fluidly connected to a combustor by a primary flow path. The turbine section includes a first portion at a high pressure relative to a second portion. A thermally isolated cooling plenum is positioned radially inward of the primary flow path. The cooling plenum is defined by a forward wall, a shaft structure, an aft wall, and an inner diameter wall of the primary flow path. Air in the thermally isolated cooling plenum is thermally isolated from air in the primary flow path. At least one cooling air system is operable to provide cooling air to the thermally isolated cooling plenum.

主权项

1. A gas turbine engine comprising:
a compressor section; a combustor fluidly connected to the compressor section by a primary flow path, wherein the primary flow path is defined by an inner diameter flow path wall and an outer diameter flow path wall; a turbine section fluidly connected to the combustor by the primary flow path, wherein the turbine section includes a first portion and a second portion, the primary flow path through the first portion has a high pressure relative to the primary flow path through the second portion; a thermally isolated cooling plenum radially inward of the primary flow path, wherein the cooling plenum is defined by a forward wall, a shaft structure, an aft wall, and an inner diameter wall of the primary flow path, and wherein air in the thermally isolated cooling plenum is thermally isolated from air in the primary flow path; and at least one cooling air system operable to provide cooling air to the thermally isolated cooling plenum.