| CPC F01D 9/041 (2013.01) [F01D 5/18 (2013.01); F05D 2220/32 (2013.01); F05D 2240/128 (2013.01)] | 18 Claims |
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1. A gas turbine engine comprising:
a compressor section configured to compress a core flow;
a combustor section comprising a combustor, wherein the combustor is arranged downstream from the compressor section along a path of the core flow;
a turbine section arranged downstream from the combustor section along the path of the core flow, wherein the turbine section comprises a plurality of first vanes arranged at an outlet of the combustor, wherein each first vane of the plurality of first vanes comprises an internal vane path; and
an integral compressor diffuser arranged radially inward from the plurality of first vanes and integrated with the plurality of first vanes, the integral compressor diffuser arranged to diffuse and direct the entire core flow from the compressor section through the internal vane path,
wherein the path of the core flow, in a flow direction, passes through the compressor section, and the entire core flow is directed from the compressor section into and through the compressor diffuser and the internal vane path to provide internal back face cooling to the plurality of first vanes, wherein the internal vane paths are configured to expand and diffuse the core flow as it passes through the internal vane paths, and
wherein the entire core flow is directed from the internal vane paths into a combustor cavity that contains the combustor for combustion with fuel, and then the combusted air and fuel is directed between the plurality of first vanes to enter the turbine section.
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