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 discoura
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.
대표청구항▼
1. 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 a
1. 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; anda 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. 2. The assembly of claim 1, wherein the flow discourager is axially spaced from the first wall of the notch and radially spaced from the second wall of the notch to form a gap having portions that extend both generally axially and generally radially with respect to a centerline axis of the gas turbine engine. 3. The assembly of claim 2, wherein the flow discourager causes the ingestion gas flow to change a flow direction in order to pass along the gap. 4. The assembly of claim 1, wherein the innermost radial surface of the second module has a radial distance from a centerline axis of the gas turbine engine that is less than a radial distance from the centerline axis of an innermost radial surface of the flow discourager such that the innermost radial surface of the second module, the first wall of the notch, and the innermost radial surface of the flow discourager form a step. 5. The assembly of claim 1, wherein the flow discourager comprises a ring with a flange and an arm extending from the flange, and wherein the arm extends generally axially with respect to a centerline axis of the gas turbine engine. 6. The assembly of claim 1, wherein the first module comprises a first outer radial casing section and the second module comprises a second outer radial casing section. 7. The assembly of claim 1, wherein an upstream end of the second module is connected to a downstream end of the first module. 8. The assembly of claim 1, wherein the flow discourager contacts the second module at one or more surfaces. 9. The assembly of claim 1, wherein affixing the flow discourager to the first module substantially restrains relative displacement between the flow discourager and the first module in an axial direction, a radial direction, and a circumferential direction. 10. 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; anda 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; anda 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. 11. The assembly of claim 10, wherein the flow discourager causes an ingestion gas flow to change a flow direction in order to pass along the gap. 12. The assembly of claim 10, wherein an innermost radial surface of the second outer radial casing section has a radial distance that differs from an innermost radial surface of the flow discourager. 13. The assembly of claim 10, wherein the flow discourager comprises a ring with a flange and an arm extending from the flange. 14. The assembly of claim 13, wherein the arm extends into a notch formed by first and second walls of the second outer radial casing, wherein the first wall extends generally radially from an innermost radial surface of the second outer radial casing, and wherein the second wall extends generally axially from an axially-facing wall of the second outer radial casing. 15. 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; anda 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. 16. The turbine section of claim 15, wherein the flow discourager is connected to the first outer radial casing and is spaced from the second outer radial casing to form a gap therebetween, the gap having both a generally axial section and a generally radial section with respect to a centerline axis of the gas turbine engine. 17. The turbine section of claim 15, wherein an upstream end of the second module is connected to a downstream end of the first module. 18. The turbine section of claim 15, wherein the flow discourager causes the ingestion gas flow to change a flow direction into a space between the first outer radial casing and the fairing.
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허에 인용된 특허 (61)
Diantonio, Gregory L., "L" butt gap seal between segments in seal assemblies.
Lenahan Dean T. (Cincinnati OH) Riedmiller Charles F. (Loveland OH) Elovic Andrew P. (Rishon Lezion ILX), Integral turbine nozzle support and discourager seal.
McNickle Alan D. (Sellersville PA) Hwang Mingfong (Lansdale PA) Pope Adam N. (Cincinnati OH), Seal for sealing an incompressible fluid between a relatively stationary seal and a movable member.
Coign,Robert Walter; Humanchuk,David John; Foster,Gregory Thomas; Worley,Kevin Lee, System for sealing an inner retainer segment and support ring in a gas turbine and methods therefor.
Zborovsky, James M.; Hsu, Johan; McQuiggan, Andrew G., Transition-to-turbine seal apparatus and kit for transition/turbine junction of a gas turbine engine.
Meade Robert J. (West Chester OH) Albrecht Richard W. (Fairfield OH) Weisgerber Robert H. (Loveland OH), Turbine disk interstage seal axial retaining ring.
Weisgerber Robert H. (Loveland OH) Albrecht Richard W. (Fairfield OH) Glynn Christopher C. (Hamilton OH) Kutney ; Jr. John T. (Cincinnati OH) Meade Robert J. (West Chester OH), Turbine disk interstage seal system.
Fledderjohn Steve R. (Cincinnati OH) Przytulski James C. (Fairfield OH) Elston ; III Sidney B. (Cincinnati OH) Gilchrist Alan R. (Fairfield OH) Hauser Ambrose A. (Wyoming OH), Turbine support assembly including turbine heat shield and bolt retainer assembly.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.