US-12618369-B2 - Propulsion engine and cowl

Abstract

A propulsion system for an aircraft including a core engine connected to a forward frame and a turbine frame assembly, and an aft frame assembly is connected by a turbine casing to the core engine aft of the turbine frame assembly. A core cowl surrounds the core engine, wherein the core cowl is connected to the forward frame. A plurality of cowl mount links selectively loads the core cowl to the aft frame assembly and the turbine frame assembly, wherein the plurality of cowl mount links is each loaded by deflection of the core engine.

Inventors

• Peeyush Pankaj
• Narayanan Payyoor
• Richard Schmidt

Assignees

• GENERAL ELECTRIC COMPANY

Dates

Publication Date

20260505

Application Date

20210901

Priority Date

20201016

Claims (19)

1. 1 . A propulsion system for an aircraft, the propulsion system defining a nominal centerline axis along an axial direction, the propulsion system comprising: a fan assembly comprising a forward frame; a core engine connected to the forward frame, wherein the core engine comprises a turbine frame assembly, and wherein the core engine defines an engine centerline axis, and further wherein the engine centerline axis is substantially coaxial to the nominal centerline axis during normal propulsion system operation, and wherein the engine centerline axis is at an acute angle to the nominal centerline axis when the core engine is deflected; an aft turbine frame assembly connected by a turbine casing to the core engine aft of the turbine frame assembly; a core cowl surrounding the core engine, wherein the core cowl is connected to the forward frame; and a plurality of cowl mount links selectively loading the core cowl to the aft turbine frame assembly and the turbine frame assembly, wherein the plurality of cowl mount links is each loaded by deflection of the core engine, wherein the plurality of cowl mount links comprise a first cowl mount link coupled to the core cowl and the aft turbine frame assembly, and wherein the plurality of cowl mount links comprise a second cowl mount link coupled to the core cowl and the turbine frame assembly, wherein the second cowl mount link is located forward of the first cowl mount link along the axial direction, wherein the aft turbine frame assembly and the turbine frame assembly each comprises a plurality of members extended along a radial direction toward the core cowl, wherein the plurality of members is configured to be selectively loaded by the plurality of cowl mount links, wherein the first cowl mount link selectively loads the core cowl to the aft turbine frame assembly, wherein the second cowl mount link selectively loads the core cowl to the turbine frame assembly, wherein the plurality of cowl mount links each comprises a coupling positioned axially forward or aft of a respective member of the plurality of members, the coupling having an arm extending radially inwardly from the core cowl and a fork attached to the arm and extending radially inwardly from the arm, the fork configured to at least partially surround the respective member, wherein a respective joint member of a plurality of joint members connects the coupling at the core cowl to the respective member, wherein the respective joint member is pivotably connected to the coupling via a first pivot point and the respective joint member is pivotably connected to the respective member of the plurality of members via a second pivot point.
2. 2 . The propulsion system of claim 1 wherein the turbine frame assembly comprises a turbine center frame casing, and wherein the aft turbine frame assembly comprises a turbine rear frame casing.
3. 3 . The propulsion system of claim 2 , wherein the coupling and the respective member are unloaded relative to one another when the engine centerline axis is substantially coaxial to the nominal centerline axis.
4. 4 . The propulsion system of claim 3 , wherein the coupling and the member are loaded onto one another when the engine centerline axis is deflected at the acute angle relative to the nominal centerline axis.
5. 5 . The propulsion system of claim 2 , wherein the respective member is extended toward the core cowl, and wherein the coupling is extended toward the respective member, and wherein the coupling and the respective member are unloaded relative to one another when the engine centerline axis is substantially coaxial to the nominal centerline axis.
6. 6 . The propulsion system of claim 5 , wherein the coupling comprises a first coupling and a second coupling, wherein the aft turbine frame assembly comprises a first member of the plurality of members extended along a radial direction toward a nacelle, and wherein the first cowl mount link of the plurality of cowl mount links comprises the first coupling extended along the radial direction toward the core engine, and wherein the turbine casing comprises a second member of the plurality of members extended toward the core cowl, and wherein the second cowl mount link of the plurality of cowl mount links comprises the second coupling extended along the radial direction toward the core engine.
7. 7 . The propulsion system of claim 6 , wherein at least a portion of the first coupling is positioned circumferentially adjacent to the first member.
8. 8 . The propulsion system of claim 6 , wherein at least a portion of the second coupling is positioned circumferentially adjacent to the second member.
9. 9 . The propulsion system of claim 6 , wherein the fork includes a portion extended circumferentially adjacent to the respective first member or second member.
10. 10 . The propulsion system of claim 2 , wherein a first joint member of the plurality of joint members connects a first member of the plurality of members to a first coupling of the plurality of cowl mount links, and wherein a second joint member of the plurality of joint members connects a second member of the plurality of members to a second coupling of the plurality of cowl mount links.
11. 11 . The propulsion system of claim 1 , wherein the plurality of cowl mount links is disposed in circumferential arrangement at the core cowl.
12. 12 . The propulsion system of claim 1 , comprising: a nacelle surrounding the core cowl, wherein the nacelle is connected to the forward frame.
13. 13 . The propulsion system of claim 12 , wherein the nacelle is connected to the core engine by an aft nacelle mount.
14. 14 . The propulsion system of claim 13 , wherein the aft nacelle mount connects the nacelle to the core engine at one or both of the turbine frame assembly or the aft turbine frame assembly, and wherein the coupling is positioned circumferentially adjacent to the respective member of the plurality of members.
15. 15 . A gas turbine engine, the gas turbine engine defining a nominal centerline axis along an axial direction, the gas turbine engine comprising: a fan assembly comprising a forward frame; a core engine connected to the forward frame, wherein the core engine comprises a turbine frame assembly, and wherein the core engine defines an engine centerline axis, and further wherein the engine centerline axis is substantially coaxial to the nominal centerline axis during normal propulsion system operation, and wherein the engine centerline axis is at an acute angle to the nominal centerline axis when the core engine is deflected; an aft turbine frame assembly, wherein the turbine frame assembly comprises a turbine center frame casing at which the aft turbine frame assembly is connected to the core engine aft of the turbine frame assembly, and wherein the aft turbine frame assembly comprises a turbine rear frame casing; a core cowl surrounding the core engine, wherein the core cowl is connected to the forward frame; and a plurality of cowl mount links selectively loading the core cowl to the aft turbine frame assembly and the turbine frame assembly, wherein the plurality of cowl mount links is each loaded by deflection of the core engine, wherein the plurality of cowl mount links comprise a first cowl mount link coupled to the core cowl and the aft turbine frame assembly, and wherein the plurality of cowl mount links comprise a second cowl mount link coupled to the core cowl and the turbine frame assembly, wherein the second cowl mount link is located forward of the first cowl mount link along the axial direction, wherein the aft turbine frame assembly and the turbine frame assembly each comprises a plurality of members extended along a radial direction toward the core cowl, and wherein the plurality of cowl mount links each comprises a coupling positioned axially forward or aft of a respective member of the plurality of members, the coupling having an arm extending radially inwardly from the core cowl and a fork attached to the arm and extending radially inwardly from the arm, the fork configured to at least partially surround the respective member, wherein a respective joint member of a plurality of joint members connects the coupling at the core cowl to a respective member of the plurality of members, wherein the respective joint member is pivotably connected to the coupling via a first pivot point and the respective joint member is pivotably connected to the respective member of the plurality of members via a second pivot point.
16. 16 . The gas turbine engine of claim 15 , wherein the plurality of members is configured to be selectively loaded by the plurality of cowl mount links, and further wherein the coupling and the respective member are unloaded relative to one another when the engine centerline axis is substantially coaxial to the nominal centerline axis, and wherein the coupling and the respective member are loaded onto one another when the engine centerline axis is deflected at the acute angle relative to the nominal centerline axis.
17. 17 . The gas turbine engine of claim 16 , comprising: a nacelle surrounding the core cowl, wherein the nacelle is connected to the forward frame, and wherein the nacelle is connected to the core engine by an aft nacelle mount, and further wherein the aft nacelle mount connects the nacelle to the core engine at one or both of the turbine frame assembly or the aft turbine frame assembly, and wherein the coupling is positioned circumferentially adjacent to the respective member of the plurality of members.
18. 18 . The gas turbine engine of claim 15 , wherein the respective member is extended toward the core cowl, the coupling is extended toward the respective member, and the coupling and the respective member are unloaded relative to one another when the engine centerline axis is substantially coaxial with the nominal centerline axis.
19. 19 . The gas turbine engine of claim 15 , wherein a first joint member of the plurality of joint members connects a first member of the plurality of members to a first coupling of the plurality of cowl mount links, and a second joint member of the plurality of joint members connects a second member of the plurality of members to a second coupling of the plurality of cowl mount links.

Description

PRIORITY INFORMATION The present application claims priority to Indian Patent Application Number 202011045065 filed on Oct. 16, 2020. FIELD The present subject matter relates generally to propulsion system cowls and mount structures therefor. BACKGROUND Propulsion engines, such as turbofan engines, include cowls surrounding a core engine or gas generator of the propulsion engine. Conventional cowl mount structures include linkages at a forward fan and an aft plane of the turbofan engine. Certain cowl mount systems, such as cantilevered cowl mounts, may result in a bending moment that would otherwise distort engine clearances are not transmitted through the core engine. However, cantilevered cowl mount systems are susceptible to excessive engine deflection following extreme aircraft maneuvers that may result from foreign object ingestion, bird strikes, blade out, or other failure modes. Excessive engine deflection may result in excessive loads at the cowl mount location, such as at the forward mount, flanges, or other attachment points. Excessive loads may manifest as engine oscillations following an extreme engine or aircraft event. However, such additional reinforcements significantly increase engine weight, which adversely impacts engine and aircraft fuel consumption. Therefore, an improved propulsion engine cowl mount system that provides improved clearance distortion characteristics and mitigates excessive deflection is desired. BRIEF DESCRIPTION Aspects and advantages of the invention will be set forth in part in the following description, or may be obvious from the description, or may be learned through practice of the invention. An aspect of the present disclosure is directed to a propulsion system for an aircraft including a core engine connected to a forward frame and a turbine frame assembly, and an aft frame assembly is connected by a turbine casing to the core engine aft of the turbine frame assembly. A core cowl surrounds the core engine, wherein the core cowl is connected to the forward frame. A plurality of cowl mount links selectively loads the core cowl to the aft frame assembly and the turbine frame assembly, wherein the plurality of cowl mount links is each loaded by deflection of the core engine. These and other features, aspects and advantages of the present invention will become better understood with reference to the following description and appended claims. The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and, together with the description, serve to explain the principles of the invention. BRIEF DESCRIPTION OF THE DRAWINGS A full and enabling disclosure of the present invention, including the best mode thereof, directed to one of ordinary skill in the art, is set forth in the specification, which makes reference to the appended figures, in which: FIG. 1 is a perspective view of an exemplary aircraft according to an aspect of the present disclosure; FIG. 2 is a cross sectional view of an exemplary embodiment of a portion of an aircraft including an exemplary embodiment of a propulsion system according to aspects of the present disclosure; FIG. 3 is a perspective view of an exemplary embodiment of a propulsion system deflecting at the airframe; FIG. 4 is a schematic view of a propulsion system including cowl mount links according to aspects of the present disclosure; FIGS. 5-9 depict embodiments of the cowl mount links of the propulsion system of FIGS. 2-4; FIG. 10 depicts an embodiment of the cowl mount link of the propulsion system of FIGS. 2-4; and FIG. 11 depicts an embodiment of the propulsion system of FIG. 10. Repeat use of reference characters in the present specification and drawings is intended to represent the same or analogous features or elements of the present invention. DETAILED DESCRIPTION Reference now will be made in detail to embodiments of the invention, one or more examples of which are illustrated in the drawings. Each example is provided by way of explanation of the invention, not limitation of the invention. In fact, it will be apparent to those skilled in the art that various modifications and variations can be made in the present invention without departing from the scope or spirit of the invention. For instance, features illustrated or described as part of one embodiment can be used with another embodiment to yield a still further embodiment. Thus, it is intended that the present invention covers such modifications and variations as come within the scope of the appended claims and their equivalents. As used herein, the terms “first”, “second”, and “third” may be used interchangeably to distinguish one component from another and are not intended to signify location or importance of the individual components. The terms “upstream” and “downstream” refer to the relative direction with respect to fluid flow in a fluid pathway. For example, “upstream” refers to the direction f