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US 10,760,491 B2Granted
Method and apparatus for handling pre-diffuser airflow for use in adjusting a temperature profile
AssigneeRaytheon Technologies Corporation
InventorsGabriel L. Suciu, William K. Ackermann
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Abstract
A gas turbine engine is provided that includes 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 in communication with said mid-span pre-diffuser inlet and said combustor section.
Claims11
A gas turbine engine comprising:
- a compressor section;
- a turbine section comprising a plurality of nozzle guide vanes;
- a combustor section between said compressor section and said turbine section, said combustor section comprising a burner;
- 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 extending radially between said inner shroud and said outer shroud, said first strut defining a mid-span pre-diffuser inlet in communication with said annular flow path, wherein said mid-span pre-diffuser inlet is located mid-span along said first strut between said inner shroud and said outer shroud;
- and
- a first manifold configured to receive an airflow from the annular flow path through the mid-span pre-diffuser inlet, and the first manifold configured to subsequently direct the airflow received through the mid-span pre-diffuser inlet to the combustor section;
- wherein said burner comprises a bulkhead and a liner assembly that extends from said bulkhead to said nozzle guide vanes, and wherein said first manifold is configured to direct said airflow received through said mid-span pre-diffuser inlet into a combustion chamber of said burner through said liner assembly forward of said nozzle guide vanes;
- wherein said first manifold is configured to direct the airflow received through the mid-span pre-diffuser inlet into the combustion chamber to generate a burner exit temperature profile;
- and
- wherein said burner exit temperature profile is an inverse of a temperature profile of an airflow from said compressor section.
7 more elements
A method of communicating an airflow within a gas turbine engine, the method comprising:
- tapping a pre-diffuser airflow as a temperature tailored airflow from a relatively cooler zone through a pre-diffuser inlet, wherein the pre-diffuser airflow comprises the relatively cooler zone and a relatively hotter zone, said pre-diffuser inlet is located radially between an inner shroud and an outer shroud in a first strut, and said first strut extends radially between and is connected to said inner shroud and said outer shroud;
- and
- directing the temperature tailored airflow received through the pre-diffuser inlet into a combustion chamber of a burner through a liner assembly of said burner forward of a plurality of nozzle guide vanes, wherein said burner is included in a combustor section of the gas turbine engine, and wherein said nozzle guide vanes are adjacent said liner assembly;
- tailoring a burner exit temperature profile associated with Ea lithe burner in the combustor section with the temperature tailored airflow;
- and
- generating a relatively cooler annular mid-span zone with respect to a relatively hotter outer diameter zone and a relatively hotter inner diameter zone of said burner exit temperature profile;
- wherein the relatively cooler annular mid-span zone comprises the relatively cooler zone;
- and
- wherein the relatively hotter outer diameter zone or the relatively hotter inner diameter zone comprises the relatively hotter zone.
6 more elements
Dependencies are inferred from the claim text.