Gas turbine engine disassembly/assembly methods
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.
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 . 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 . 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 . The method of claim 2 , wherein the second turbine rotor includes a second turbine section case.
5 . The method of claim 1 , wherein the turbine support structure comprises a mid-turbine frame.
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 . 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 . The method of claim 1 , wherein the gas turbine engine assembly is installed with an aircraft.
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 . The method of claim 9 , further comprising connecting the one or more external components to the turbine support structure.
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 . The method of claim 11 , wherein the gas turbine engine assembly is mounted on a wing or a fuselage of the aircraft.
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 . 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 . 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.