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US 10,704,468 B2Granted
Method and apparatus for handling pre-diffuser airflow for cooling high pressure turbine components
AssigneeRaytheon Technologies Corporation
InventorsGabriel L. Suciu, William K. Ackermann
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Abstract
A gas turbine engine is provided comprising a compressor section, a combustor section, a diffuser case module, and a manifold. The diffuser case module includes a multiple of struts within an annular flow path from said compressor section to said combustor section, wherein at least one of said multiple of struts defines a mid-span pre-diffuser inlet in communication with said annular flow path. The manifold is in communication with said mid-span pre-diffuser inlet and said compressor section.
Claims14
A gas turbine engine comprising:
- a compressor section;
- a combustor section;
- a diffuser case module comprising an inner shroud, an outer shroud and a multiple of struts within an annular flow path from said compressor section to said combustor section, said multiple of struts comprising a first strut that extends radially between said inner shroud and said outer shroud, wherein said first strut includes a leading edge, a trailing edge and an outer wall surface extending between the leading edge and the trailing edge, wherein said first strut defines a mid-span pre-diffuser inlet in communication with said annular flow path, and wherein said mid-span pre-diffuser inlet is on a side of the first strut and in the outer wall surface;
- and
- a manifold in communication with said mid-span pre-diffuser inlet and said compressor section;
- wherein said first strut has a circumferential width that increases as said first strut extends from said leading edge to said trailing edge such that said circumferential width has a first value at said leading edge that is less than a second value of said circumferential width at said trailing edge.
3 more elements
A gas turbine engine comprising:
- a compressor section;
- a combustor section;
- a diffuser case module comprising an inner shroud, an outer shroud and a multiple of struts within an annular flow path from said compressor section to said combustor section, said multiple of struts comprising a first strut that extends radially between said inner shroud and said outer shroud, wherein said first strut includes a leading edge, a trailing edge and an outer wall surface extending between the leading edge and the trailing edge, wherein said first strut defines a mid-span pre-diffuser inlet in communication with said annular flow path, and wherein said mid-span pre-diffuser inlet is on a side of the first strut and in the outer wall surface;
- and
- a manifold in communication with said mid-span pre-diffuser inlet and said compressor section;
- wherein said first strut has a maximum circumferential width at a first location along a longitudinal length of said first strut, and said first location is at said trailing edge;
- and
- wherein said mid-span pre-diffuser inlet is located at a second location along said longitudinal length of said first strut where said first strut has a second circumferential width that is less than said maximum circumferential width.
5 more elements
A gas turbine engine comprising:
- a compressor section;
- a combustor section;
- a diffuser case module comprising an inner shroud, an outer shroud and a multiple of struts within an annular flow path from said compressor section to said combustor section, said multiple of struts comprising a first strut that extends radially between said inner shroud and said outer shroud, wherein said first strut includes a leading edge, a trailing edge and an outer wall surface extending between the leading edge and the trailing edge, wherein said first strut defines a mid-span pre-diffuser inlet in communication with said annular flow path, and wherein said mid-span pre-diffuser inlet is on a side of the first strut and in the outer wall surface;
- and
- a manifold in communication with said mid-span pre-diffuser inlet and said compressor section such that said compressor section is fluidly coupled with said mid-span pre-diffuser inlet through said manifold;
- wherein said mid-span pre-diffuser inlet comprises a scoop that projects into said annular flow path from said side of said first strut;
- wherein said first strut has a maximum circumferential width at a first location along a longitudinal length of said first strut, and said first location is at said trailing edge;
- and
- wherein said mid-span pre-diffuser inlet is located at a second location along said longitudinal length of said first strut where said first strut has a second circumferential width that is less than said maximum circumferential width.
6 more elements
Dependencies are inferred from the claim text.