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US 2010/0247304 A1Published application
Exhaust plenum for a turbine engine
AssigneeGeneral Electric Company
InventorsLaxmikant Merchant, Prabhakaran Saraswathi Rajesh
Life of this patent
Estimating the term…
Abstract
An exhaust system for gas turbine engine is provided that reduces turbulence and backflow within the exhaust system and, thus, increases the efficiency of the turbine engine. In various embodiments, the system includes an exhaust plenum that provides a gradual expansion of the exhaust gases. The exhaust plenum may also include one or more flow splitters that further reduce turbulence in the plenum and provide a more uniform gas flow in the plenum and other downstream exhaust components.
Claims20
A system, comprising:
- a turbine engine comprising a radial diffuser disposed about a first axis downstream in an exhaust flow path from a turbine section;
- and
- an exhaust plenum, comprising:
- an inlet, wherein the radial diffuser is disposed through the inlet into the exhaust plenum, and the exhaust plenum extends along a second axis crosswise relative to the first axis of the turbine engine;
- a flow splitter extending completely across the exhaust plenum along the first axis, wherein the flow splitter extends in a first direction radially outward from the radial diffuser relative to the first axis, and the flow splitter bends from the first direction to a second direction downstream along the second axis;
- and
- a set of first and second aerodynamic surfaces facing one another about the radial diffuser, wherein the first and second aerodynamic surfaces are axially offset from one another by an axial offset along the first axis, and the first and second aerodynamic surfaces gradually expand the axial offset with increasing radial distance away from the first axis.
4 more elements
A system, comprising:
- a turbine exhaust plenum, comprising:
- an inlet coupled to a diffuser region configured to receive a radial diffuser of a turbine engine along a first axis, wherein the turbine exhaust plenum extends along a second axis crosswise relative to the first axis;
- and
- a flow splitter extending completely across the turbine exhaust plenum along the first axis adjacent the diffuser region, wherein the flow splitter extends from an upstream end to a downstream end with a length of at least greater than a radius of the radial diffuser, and the flow splitter bends from the upstream end to the downstream end over an angle of at least approximately 90 degrees.
1 more element
A system, comprising:
- a turbine exhaust plenum, comprising:
- an inlet coupled to a diffuser region configured to receive a radial diffuser of a turbine engine along a first axis, wherein the turbine exhaust plenum extends along a second axis crosswise relative to the first axis;
- and
- a set of first and second aerodynamic surfaces disposed opposite from one another relative to the diffuser region, wherein the first and second aerodynamic surfaces diverge away from one another in an outward radial direction away from the first axis.
1 more element
Dependencies are inferred from the claim text.