US-12618341-B2 - Gas turbine engine disassembly/assembly methods

Abstract

A method is provided for disassembling a gas turbine engine. The gas turbine engine includes a compressor section, a combustor section, a turbine section, a static structure and a bypass duct. The static structure houses and supports the compressor section, the combustor section and the turbine section. The static structure includes a turbine support structure. The bypass duct includes an inner duct wall, an outer duct wall and a bypass flowpath formed radially between the inner duct wall and the outer duct wall. The outer duct wall extends axially along the static structure and overlaps the turbine support structure. During the method, the turbine support structure is removed from the gas turbine engine while the outer duct wall remains installed.

Inventors

• Carlo S. Porco
• Geoffrey Henriksen
• Jason WEDEMIRE
• Anthony MATHIAS
• Michael Hunze
• Louis Lavoie
• Marven Paynter
• Dennis Wilkinson

Assignees

• PRATT & WHITNEY CANADA CORP.

Dates

Publication Date

20260505

Application Date

20230814

Claims (15)

1. 1 . A method for assembling a gas turbine engine, comprising: providing a gas turbine engine assembly that includes a compressor rotor; a combustor; a turbine rotor; a forward portion of a static structure housing and supporting the compressor rotor, the combustor and the turbine rotor; and a bypass duct including an inner duct wall, an outer duct wall and a bypass flowpath formed radially between the inner duct wall and the outer duct wall, the outer duct wall axially overlapping the combustor, the turbine rotor and the forward portion of the static structure; providing a turbine support structure, the turbine support structure previously assembled then disconnected from the gas turbine engine assembly; and reassembling the turbine support structure with the gas turbine engine assembly such that the turbine support structure is fastened to the forward portion of the static structure and the outer duct wall axially overlaps the turbine support structure; wherein the outer duct wall remains installed during the step of reassembling the turbine support structure with the gas turbine engine assembly.
2. 2 . The method of claim 1 , further comprising assembling a second turbine rotor with the gas turbine engine assembly, wherein the turbine support structure is arranged axially between the turbine rotor and the second turbine rotor following the assembling of the second turbine rotor.
3. 3 . The method of claim 2 , further comprising assembling an exhaust structure with the gas turbine engine assembly, wherein the second turbine rotor is arranged axially between the turbine support structure and the exhaust structure following the assembling of the exhaust structure.
4. 4 . The method of claim 2 , wherein the second turbine rotor includes a second turbine section case.
5. 5 . The method of claim 1 , wherein the turbine support structure comprises a mid-turbine frame.
6. 6 . The method of claim 1 , further comprising assembling one or more panels comprising the inner duct wall of the gas turbine engine assembly.
7. 7 . The method of claim 1 , wherein the gas turbine engine assembly further comprises a fan section and a fan case housing the fan section, and the outer duct wall is connected to the fan case.
8. 8 . The method of claim 1 , wherein the gas turbine engine assembly is installed with an aircraft.
9. 9 . The method of claim 1 , wherein one or more external components are configured with the forward portion of the static structure that is connected to the outer duct wall prior to the step of reassembling the turbine support structure with the gas turbine engine assembly.
10. 10 . The method of claim 9 , further comprising connecting the one or more external components to the turbine support structure.
11. 11 . A method for assembling a gas turbine engine, comprising: providing an aircraft and a gas turbine engine assembly installed with the aircraft, the gas turbine engine assembly including a compressor rotor, a combustor, a turbine rotor, a forward portion of a static structure and a bypass duct, the forward portion of the static structure housing and supporting the compressor rotor, the combustor and the turbine rotor, the bypass duct including an inner duct wall, an outer duct wall and a bypass flowpath formed radially between the inner duct wall and the outer duct wall, and the outer duct wall axially overlapping the combustor, the turbine rotor and the forward portion of the static structure; providing a turbine support structure at a location outside of the aircraft, the turbine support structure previously assembled then disconnected from the gas turbine engine assembly; providing a second turbine rotor at the location outside of the aircraft, the second turbine rotor previously assembled then disconnected from the gas turbine engine assembly; reassembling the turbine support structure with the gas turbine engine assembly such that the turbine support structure is fastened to the forward portion of the static structure and the outer duct wall axially overlaps the turbine support structure; and reassembling the second turbine rotor with the gas turbine engine assembly, wherein the turbine support structure is arranged axially between the turbine rotor and the second turbine rotor following the assembling of the second turbine rotor; wherein the outer duct wall remains installed during the step of reassembling the turbine support structure with the gas turbine engine assembly.
12. 12 . The method of claim 11 , wherein the gas turbine engine assembly is mounted on a wing or a fuselage of the aircraft.
13. 13 . The method of claim 11 , further comprising assembling one or more panels comprising the inner duct wall of the gas turbine engine assembly.
14. 14 . The method of claim 11 , wherein the gas turbine engine assembly further comprises a fan section and a fan case housing the fan section, and the outer duct wall is connected to the fan case.
15. 15 . The method of claim 11 , further comprising assembling an exhaust structure with the gas turbine engine assembly, wherein the second turbine rotor is arranged axially between the turbine support structure and the exhaust structure following the assembling of the exhaust structure.

Description

This application is a divisional of U.S. patent application Ser. No. 17/388,865 filed Jul. 29, 2021, which is hereby incorporated herein by reference in its entirety. BACKGROUND OF THE DISCLOSURE 1. Technical Field This disclosure relates generally to a gas turbine engine and, more particularly, to methods for disassembling and assembling the turbine engine. 2. Background Information A gas turbine engine is a complex system with various different sections, modules and components. There is a need to inspect, repair and/or replace various components within the turbine engine. Thus, from time to time, the turbine engine may be disassembled to remove the desired components for inspection, repair and/or replacements. There are various methods known in the art for disassembling and then reassembling a gas turbine engine to remove and then install/reinstall various components. While these known methods have various advantages, there is still room in the art for improvement. For example, there is a need for a method of removing an internal component from a gas turbine engine such as a mid-turbine frame without significantly disassembling other sections, modules and/or structures of the turbine engine. SUMMARY OF THE DISCLOSURE According to an aspect of the present disclosure, an engine disassembly method is provided. During this method, a gas turbine engine is provided. This gas turbine engine includes a compressor section, a combustor section, a turbine section, a static structure and a bypass duct. The static structure houses and supports the compressor section, the combustor section and the turbine section. The static structure includes a turbine support structure. The bypass duct includes an inner duct wall, an outer duct wall and a bypass flowpath formed radially between the inner duct wall and the outer duct wall. The outer duct wall extends axially along the static structure and overlaps the turbine support structure. The turbine support structure is removed from the gas turbine engine while the outer duct wall remains installed. According to another aspect of the present disclosure, another engine disassembly method is provided. During this method, a gas turbine engine is provided. This gas turbine engine includes a compressor section, a combustor section, a turbine section and a static structure. The turbine section includes a first turbine rotor and a second turbine rotor. The static structure houses and supports the compressor section, the combustor section and the turbine section. The static structure includes a turbine support structure arranged axially between the first turbine rotor and the second turbine rotor. The second turbine rotor is removed from the gas turbine engine. The turbine support structure is removed from the gas turbine engine without removing the first turbine rotor. According to still another aspect of the present disclosure, a method is provided for assembling a gas turbine engine. During this method, a gas turbine engine assembly is provided that includes a compressor rotor, a combustor, a turbine rotor, a forward portion of a static structure and an outer duct wall. The forward portion of the static structure houses and supports the compressor rotor, the combustor and the turbine rotor. The outer duct wall axially overlaps the combustor, the turbine rotor and the forward portion of the static structure. A turbine support structure is provided. The turbine support structure is assembled with the gas turbine engine assembly such that the turbine support structure is fastened to the forward portion of the static structure and the outer duct wall axially overlaps the turbine support structure. The method may include assembling a second turbine rotor with the gas turbine engine assembly. The turbine support structure may be arranged axially between the turbine rotor and the second turbine rotor following the assembling of the second turbine rotor. The gas turbine engine may also include an outer duct wall that axially overlaps the turbine support structure and the second turbine rotor when the gas turbine engine is fully assembled. The outer duct wall may be connected to a forward portion of the static structure during the removing of the second turbine rotor and the removing of the turbine support structure. The turbine support structure may be configured as or otherwise include a mid-turbine frame. When the turbine support structure is removed from the gas turbine engine: the outer duct wall may be attached to a forward portion of the static structure; and the combustor section may be housed within and supported by the forward portion of the static structure. The compressor section may include a compressor rotor. The compressor rotor may be housed within and supported by the forward portion of the static structure when the turbine support structure is removed from the gas turbine engine. The turbine section may include a turbine rotor. The turbine rotor may be housed within and sup