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US 9,541,006 B2Granted
Inter-module flow discourager
AssigneeUnited Technologies Corporation
InventorsConway Chuong, Matthew Budnick
Life of this patent
Estimating the term…
Abstract
An assembly for a gas turbine engine includes a first module, a second module, and a flow discourager. The second module is connected to the first module along a joint. The flow discourager is connected to the first module and extends to be received in a notch in the second module. The flow discourager acts to direct an ingestion gas flow away from the joint between the first module and the second module.
Claims18
An assembly for a gas turbine engine, comprising:
- a first module comprising a turbine frame;
- a second module connected to the first module along a joint, wherein the second module has a notch adjacent to the joint, and wherein the notch is formed by a first wall extending generally radially from an innermost radial surface of the second module and a second wall extending generally axially from an axially-facing wall of the second module;
- and
- a flow discourager affixed to the first module and extending to be received in the notch in the second module, wherein the flow discourager directs an ingestion gas flow away from the joint between the first module and the second module and into a space between the turbine frame and an outer radial platform of a fairing disposed radially inward from the turbine frame and adapted to surround a strut extending through the fairing.
1 more element
An assembly for a gas turbine engine, comprising:
- a first outer radial casing section;
- a first inner radial casing section;
- a strut extending from the first inner radial casing section to the first outer radial casing section;
- and
- a fairing surrounding the strut to define a main gas flow path;
- a second outer radial casing section connected to the first outer radial casing section;
- and
- a flow discourager mounted to the first outer radial casing section and extending to form a contactless interface with the second outer radial casing section, wherein a distal end of the flow discourager is spaced from the second outer radial casing section to form a gap therebetween, the gap having both a generally axial portion and a generally radial portion with respect to a centerline axis of the gas turbine engine, and wherein the flow discourager is configured to direct an ingestion gas flow into a space between the first outer radial casing section and an outer radial platform of the fairing.
5 more elements
A turbine section for a gas turbine engine, comprising:
- a first module comprising:
- a first outer radial casing section;
- a first inner radial casing section;
- a strut extending from the first inner radial casing section to the first outer radial casing section;
- and
- a fairing surrounding the strut to define a main gas flow path;
- a second module having a second outer radial casing section connected to the first outer radial casing section;
- a flow discourager that is disposed radially outward from both the fairing and the main gas flow path of the gas turbine engine and extends from the first outer radial casing section towards the second outer radial casing section to form a contactless interface therewith, wherein an innermost radial surface of the second outer radial casing section has a radial distance from a centerline axis of that gas turbine engine that differs from a radial distance of an innermost radial surface of the flow discourager in order to reduce an ingestion gas flow into an area between the first outer radial casing section and the second outer radial casing section.
5 more elements
Dependencies are inferred from the claim text.