CN-121993295-A - Turbine engine frame assembly with mounting bracket assembly

Abstract

A frame assembly includes a frame and a mounting bracket assembly. The frame includes an inner hub, an outer shell positioned opposite the inner hub, and a plurality of struts connecting the inner hub with the outer shell. At least one of the plurality of struts is a hollow strut having a radial passage extending therethrough. The mounting bracket assembly includes an inner flange on an inner surface of the inner hub, an outer flange on an outer surface of the outer shell, and a radial linkage connecting the inner flange and the outer flange. The radial linkage extends through a radial passage of the hollow strut.

Inventors

• Wei .wu
• Nicholas J. clay
• Aaron M. Gilbert
• XIE MING

Assignees

• 通用电气公司

Dates

Publication Date

20260508

Application Date

20251031

Priority Date

20241101

Claims (10)

1. 1. A frame assembly for a turbine engine of an aircraft, the frame assembly having a radial direction and comprising: A frame, the frame comprising: an inner hub having an inner surface; A housing positioned opposite the inner hub and having an outer surface, and A plurality of struts connecting the inner hub with the outer casing, at least one strut of the plurality of struts extending in the radial direction being a hollow strut having a radial passage extending therethrough extending from an outer opening formed in the outer surface of the outer casing to an inner opening formed in the inner surface of the inner hub, and A mounting bracket assembly, the mounting bracket assembly comprising: an inner flange located on the inner surface of the inner hub; An outer flange located on the outer surface of the housing, and A radial linkage connecting the inner flange and the outer flange, the radial linkage extending through the radial passage of the hollow strut.
2. 2. The frame assembly of claim 1, wherein the radial linkage is of unitary construction with at least one of the inner flange or the outer flange.
3. 3. The frame assembly of claim 1, wherein the radial linkage is of unitary construction with the inner flange.
4. 4. The frame assembly of claim 1, wherein the radial linkage includes an inner end portion having one or more flange connectors, and Wherein the inner flange comprises a plurality of sections, each section being engageable with the one or more flange connectors of the inner end portion to connect the inner flange with the radial linkage.
5. 5. The frame assembly of claim 4, wherein each section of the inner flange is secured to the inner hub by fasteners engaged with both the inner flange and the inner hub.
6. 6. The frame assembly according to claim 1, wherein the hollow strut is a first hollow strut and the mounting bracket assembly is a first mounting bracket assembly, wherein the inner flange is a first inner flange, the outer flange is a first outer flange, and the radial linkage is a first radial linkage, Wherein the plurality of struts include a second hollow strut having a radial passage extending therethrough, the radial passage of the second hollow strut extending from an outer opening formed in the outer surface of the housing to an inner opening formed in the inner surface of the inner hub, and Wherein the frame assembly further comprises a second mounting bracket assembly comprising: a second inner flange located on the inner surface of the inner hub; a second outer flange located on the outer surface of the housing, and A second radial linkage connects the second inner flange with the second outer flange, the second radial linkage extending through the radial passage of the second hollow strut.
7. 7. The frame assembly of claim 6, wherein the first outer flange and the second outer flange are integrally formed with one another.
8. 8. The frame assembly of claim 6, wherein the first outer flange and the second outer flange are secured to one another.
9. 9. The frame assembly of claim 6, wherein the first outer flange and the second outer flange are secured to one another by a hinge.
10. 10. The frame assembly of claim 1, wherein the frame comprises a composite material including a plurality of reinforcing fibers positioned to embed at least a portion of the mounting bracket assembly within the frame.

Description

Turbine engine frame assembly with mounting bracket assembly Cross Reference to Related Applications The present application claims the benefit of U.S. provisional patent application No. 63/715,155 filed on 1 month 11 of 2024, which is incorporated herein by reference in its entirety. Technical Field The present disclosure relates to a frame assembly, in particular for an aircraft engine. Background Turbine engines used in aircraft typically include a fan, a compressor section, a combustion section, and a turbine section. The combustor of the combustion section generates combustion gases for driving one or more turbines of the turbine section, and the turbines may be used to drive fans. A portion of the air flowing into the fan flows through the compressor section, the combustion section, and the turbine section as core air, while another portion of the air flowing into the fan bypasses these sections and flows through the turbine engine as bypass air. The compressor section may include one or more compressors, also driven by the turbine, to compress the core air before it flows into the combustor. The composite materials may be used to manufacture various components of a turbine engine, particularly when the turbine engine is a turbine engine for an aircraft. Drawings Features and advantages of the present disclosure will become apparent from the following description of various exemplary embodiments, as illustrated in the accompanying drawings in which like reference numbers generally indicate identical, functionally similar, and/or structurally similar elements. FIG. 1 is a schematic cross-sectional view of a turbine engine for an aircraft. Fig. 2A is a schematic illustration of a three-dimensional fiber weave pattern. FIG. 2B is a schematic cross-sectional view of the fiber weave pattern shown in FIG. 2A, taken along line 2B-2B in FIG. 2A. Fig. 2C is a schematic cross-sectional view of a fiber weave pattern shown similar to the fiber weave pattern shown in fig. 2A but with a different interlocking fiber pattern. Fig. 2D is a schematic cross-sectional view of a fiber weave pattern similar to that shown in fig. 2A but having another interlocking fiber pattern. FIG. 3 is a flow chart of a general process for manufacturing a composite component that may be used in the turbine engine of FIG. 1. FIG. 4 is a schematic rear view of a guide vane structure that may be used in the turbine engine of FIG. 1. FIG. 5 is a schematic view of the guide vane structure of FIG. 4 with the mounting bracket assembly omitted for clarity. FIG. 6 is a schematic cross-sectional view of a portion of the guide vane structure shown in FIG. 4, taken along line 6-6 in FIG. 4. FIG. 7 is a schematic cross-sectional view of a portion of a guide vane structure with a mounting bracket assembly taken from a perspective similar to FIG. 6. FIG. 8 is a schematic cross-sectional view of an inner portion of a guide vane structure and an inner portion of a mounting bracket assembly. FIG. 9A is a schematic cross-sectional view of an inner portion of a guide vane structure and an inner portion of a mounting bracket assembly. FIG. 9B is a schematic cross-sectional view of a portion of the inner portion of the guide vane structure and the inner portion of the mounting bracket assembly shown in FIG. 9A, taken along line 9B-9B in FIG. 9A. FIG. 10A is a schematic cross-sectional view of an outer portion of a guide vane structure and an outer portion of a mounting bracket assembly. FIG. 10B is a schematic cross-sectional view of a portion of the upper portion of the guide vane structure and the upper portion of the mounting bracket assembly shown in FIG. 10A, taken along line 10B-10B in FIG. 10A. FIG. 11 is a schematic cross-sectional view of a portion of a guide vane structure with an alternative mounting bracket assembly taken from a perspective similar to FIG. 6. FIG. 12 is a schematic cross-sectional view of a portion of a guide vane structure with an alternative mounting bracket assembly taken from a perspective similar to FIG. 6. Fig. 13 is a flow chart of a method of forming a frame assembly. Fig. 14 is a flow chart of another method of forming a frame assembly. Detailed Description The features, advantages, and embodiments of the present disclosure are set forth or apparent from consideration of the following detailed description, drawings, and claims. Moreover, the following detailed description is exemplary and is intended to provide further explanation without limiting the scope of the disclosure as claimed. Various embodiments are discussed in detail below. Although specific embodiments are discussed, this is for illustrative purposes only. One skilled in the relevant art will recognize that other components and configurations may be used without departing from the disclosure. As used herein, the terms "first," "second," and "third" may be used interchangeably to distinguish one component from another and are not intended to represent the loc