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US 2017/0362947 A1Published application
Service routing configuration for a gas turbine engine diffuser system
AssigneeHoneywell International Inc.
InventorsShakeel Nasir, John Schugardt, Justin Brown, Cristopher Frost
Life of this patent
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Abstract
Provided is a radial diffuser that includes a housing, a plurality of diffuser vanes, and a plurality of deswirl vanes and at least one vane extension providing a service routing. Each of the vane extensions is disposed after a radial section and may extend into or through a transition and into the deswirl cascade. At least a portion of the vane extensions include a service passage extending therethrough. Each service passage is configured to allow a service conduit to extend therethrough without adversely crossing either a diffusion flow passage or a transition flow passage.
Claims20
A radial diffuser for directing a flow of compressed air with a radial component to a diffused annular flow having an axial component, the radial diffuser comprising:
- a housing including an air inlet and an air outlet, and defining a radial section extending at least substantially radially outward from the air inlet to a transition between the air inlet and air outlet, an axial section extending at least substantially axially from the transition to the air outlet, the transition including a bend and extending between the radial section and the axial section;
- and
- a plurality of diffuser vanes coupled to the housing and extending through the radial section, the plurality of diffuser vanes defining a plurality of diffusion flow passages through the radial section, deswirl cascade having a plurality of deswirl vanes and coupled to the housing after the bend in the transition, and vane extension disposed after the radial section and extending into the deswirl cascade, wherein at least a portion of the vane extensions include a service passage extending therethrough, each service passage being configured to allow a service conduit to extend therethrough.
A gas turbine engine, comprising:
- an engine housing;
- a compressor, a combustor, and a turbine all mounted in flow series within the housing, the compressor including at least:
- a compressor housing;
- an impeller rotationally mounted within the compressor housing and having a leading edge and a trailing edge, the impeller operable, upon rotation thereof, to discharge a flow of air having a velocity magnitude and a pressure magnitude from the trailing edge;
- and a radial diffuser for directing a flow of compressed air with a radial component to a diffused annular flow having an axial component, the radial diffuser comprising:
- a housing including an air inlet and an air outlet, and defining a radial section extending at least substantially radially outward from the air inlet to a transition between the air inlet and air outlet, an axial section extending at least substantially axially from the transition to the air outlet, the transition including a bend and extending between the radial section and the axial section;
- and
- a plurality of diffuser vanes coupled to the housing and extending through the radial section, the plurality of diffuser vanes defining a plurality of diffusion flow passages through the radial section, deswirl cascade having a plurality of deswirl vanes and coupled to the housing after the bend in the transition, and vane extension disposed after the radial section and extending into the deswirl cascade, wherein at least a portion of the vane extensions include a service passage extending therethrough, each service passage being configured to allow a service conduit to extend therethrough.
5 more elements
A compressor system comprising a compressor housing;
- an impeller rotationally mounted within the compressor housing and having a leading edge and a trailing edge, the impeller operable, upon rotation thereof, to discharge a flow of air having a velocity magnitude and a pressure magnitude from the trailing edge;
- and a radial diffuser for directing a flow of compressed air with a radial component to a diffused annular flow having an axial component, the radial diffuser comprising:
- a housing including an air inlet and an air outlet, and defining a radial section extending at least substantially radially outward from the air inlet to a transition between the air inlet and air outlet, an axial section extending at least substantially axially from the transition to the air outlet, the transition including a bend and extending between the radial section and the axial section;
- and
- a plurality of diffuser vanes coupled to the housing and extending through the radial section, the plurality of diffuser vanes defining a plurality of diffusion flow passages through the radial section, deswirl cascade having a plurality of deswirl vanes and coupled to the housing after the bend in the transition, and vane extension disposed after the radial section and extending into the deswirl cascade, wherein at least a portion of the vane extensions include a service passage extending therethrough, each service passage being configured to allow a service conduit to extend therethrough.
2 more elements
Dependencies are inferred from the claim text.