Method of disassembly for a gas turbine engine

• US 4,685,286 A
• Filed: 11/26/1985
• Issued: 08/11/1987
• Est. Priority Date: 05/02/1984
• Status: Expired due to Term

• Current Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Miller, Guy W., Hetzer, Frederick C.
• Primary Examiner(s): Casaregola, Louis J.
• Assistant Examiner(s): Thorpe, Timothy S.
• Application Number:
  US06/801,971
• Time in Patent Office: 623 Days
• Field of Search: 60/39.02, 60/39.31, 60/39.161, 60/268, 415/189
• US Class Current: 60/772
• CPC Class Codes: F01D 25/285 Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such structures
• CPC Class Codes: F02C 7/20 Mounting or supporting of plant; Accommodating heat expansion or creep

Abstract

A rotor assembly 22 for a gas turbine engine is disclosed. The engine has a compression section 12 and a turbine section 16. Various construction details which enable the modular disassembly of the turbine section are developed. The rotor assembly includes a rotor shaft 42 extending between the compression section and the turbine section. An annular shaft 66 engages a bearing 64, is joined to a rotor blade assembly 74, and rotatably supports the rotor shaft 42.

Claims

1. In a method of disassembling an axial flow gas turbine engine having a rotor shaft, a rotor blade assembly, an outer case, a bearing supported from the outer case which is adapted to engage an annular second shaft and to support only said rotor shaft and said annular second shaft, and an annular second shaft which is joined to the rotor blade assembly, wherein the annular second shaft engages the bearing to support only the rotor blade assembly and said rotor shaft, and wherein the annular second shaft is capable of movement in the axial direction with respect to the rotor shaft, and is coupled to the rotor shaft in the axial and circumferential directions, an improvement comprising the steps of:

uncoupling the rotor shaft and the annular second shaft-rotor blade assembly;

separating the rotor shaft and the rotor blade assembly by relative movement between the shafts in the axial direction to provide access to the interior of the engine;

supporting the rotor blade assembly from the outer case through the annular second shaft after separating the second shaft and the rotor shaft to avoid relative radial movement between the outer case and the rotor blade assembly during disassembly.

2. The method of disassembling the gas turbine engine of claim 1 wherein the turbine section includes a low pressure turbine, the rotor blade assembly is in the low pressure turbine, and the outer case in the turbine section includes a casing which is attached to an adjacent portion of the outer case and which extends circumferentially about the rotor blade assembly, and wherein the turbine section includes a bearing support which extends inwardly from the casing to support the bearing, wherein the step of separating the rotor shaft and the second shaft-rotor blade assembly includes the step of detaching the casing in the turbine section from the adjacent upstream portion of the outer case to enable the casing, the annular second shaft and the rotor blade assembly to act as a modular unit during disassembly and includes the step of separating the rotor shaft and the annular second shaft of the modular unit while supporting the rotor blade assembly of the low pressure turbine from the casing to avoid relative radial movement between the rotor blade assembly and the casing.

3. The method of disassembling the gas turbine engine of claim 2 wherein the casing includes a low pressure turbine case having a forward end which is attached to the adjacent portion of the outer case and wherein the bearing support extends inwardly from the low pressure turbine case such that the step of detaching the casing in the turbine section detaches the low pressure turbine case from the adjacent portion of the engine to enable separation of the low pressure turbine as a modular unit from the rotor shaft.

4. The method of disassembling the gas turbine engine of claim 2 wherein the casing includes a turbine exhaust case and a low pressure turbine case having an aft end attached to the turbine exhaust case and having a forward end which is attached to the adjacent portion of the outer case and wherein the bearing support extends inwardly from the exhaust case such that the step of detaching the casing in the turbine section detaches the low pressure turbine case from the adjacent portion of the engine to enable separation of the low pressure turbine and turbine exhaust case as a modular unit from the rotor shaft.

5. The method of disassembling the gas turbine engine of claim 1 wherein the turbine section includes a low pressure turbine, the rotor blade assembly is in the low pressure turbine, and the outer case in the turbine section includes a casing having a low pressure turbine case which is attached to an adjacent portion of the outer case and which extends circumferentially about the rotor blade assembly, and wherein the turbine section includes a bearing support which extends inwardly from the outer case forwardly of the low pressure turbine case to support the bearing, wherein the method of disassembling the engine includes the step of detaching the the low pressure turbine case in the turbine section from the adjacent upstream portion of the outer case to enable the low pressure turbine case, the annular second shaft, and the rotor blade assembly to act as a modular unit during disassembly, and wherein the step of supporting the rotor blade assembly from the outer case through the annular second shaft includes the further step of attaching a fixture to the casing which engages the annular second shaft and engages the casing and the further step of rigidly interconnecting the second shaft and the casing with the fixture to avoid relative radial movement between the rotor blade assembly and the casing.

6. The method of disassembling the gas turbine engine of claim 5 wherein the second annular shaft includes a first element which engages the bearing and includes a second element which is attached to the first element and which is attached to the rotor blade assembly, wherein the step of separating the rotor shaft and rotor blade assembly includes the step of separating the first and second elements and wherein the step of rigidly interconnecting the second shaft and the casing includes the step of attaching the fixture to the second element.

7. In a method of disassembling an axial flow gas turbine engine having a turbine section, an outer case having a casing in the turbine section, a low pressure turbine in the turbine section which includes a low rotor shaft, a first rotor blade assembly, a first bearing supported from the outer case, and an annular second shaft in the turbine section which is joined to the first rotor blade assembly, wherein the annular second shaft engages the bearing to support the rotor blade assembly, is capable of movement in the axial direction with respect to the rotor shaft and is coupled to the rotor shaft in the axial and circumferential directions, the engine further having a high pressure turbine which includes a high rotor shaft radially outward of and circumferentially disposed about the low rotor shaft, a second rotor blade assembly, and an annular third shaft which is joined to the second rotor blade assembly, wherein the annular third shaft is capable of movement in the axial direction with respect to the high rotor shaft and is coupled to the high rotor shaft in the axial and circumferential directions, the engine further having a second bearing which is supported from the outer case of the engine and which is adapted to engage one of said shafts in the high pressure turbine, the improvement which comprises the steps of:

uncoupling the low rotor shaft from the annular second shaft;

separating the low rotor shaft and the second shaft- first rotor blade assembly by relative movement between the shafts in the axial direction;

supporting the first rotor blade assembly from the outer case through the annular second shaft after separating the second shaft and the low rotor shaft;

withdrawing the low rotor shaft from the low pressure turbine to provide access to the coupling between the high rotor shaft and the annular third shaft;

uncoupling the high rotor shaft from the annular third shaft;

supporting the second rotor blade assembly from the outer case;

detaching the casing from the adjacent portion of the outer case;

separating the turbine section of the engine as a modular unit from the adjacent portion of the engine by relative movement between the casing, the annular third shaft-second rotor blade assembly and the adjacent portion of the engine in the axial direction.

8. The method of disassembling a gas turbine engine as claimed in claim 7 wherein the second bearing engages the third annular shaft and the engine further has a support for the second bearing which extends inwardly from the casing in the turbine section and wherein the step of supporting the second rotor blade assembly includes the step of supporting the second rotor blade assembly through the second bearing to avoid fixturing the second rotor blade assembly to the outer case.

9. The method of disassembling a gas turbine engine as claimed in claim 7 wherein the second bearing engages the high rotor shaft and the engine further has a support for the second bearing which extends inwardly from the outer case forwardly of the turbine section and wherein the step of supporting the second rotor blade assembly from the outer case includes the steps of inserting a fixture which extends through the second annular shaft to engage the third annular shaft and extends outwardly to engage the outer case and includes the step of rigidly interconnecting the third annular shaft and the outer case during relative movement between the turbine section and the remainder of the engine.

10. In a method of disassembling an axial flow gas turbine engine having a compression section, a turbine section, a rotor shaft extending between the compression section and the turbine section, and an outer case spaced radially from the rotor shaft which extends axially through the sections of the engine, the turbine section including a rotor blade assembly, a rear bearing supported from the outer case of the engine and a rear annular second shaft which is joined to the rotor blade assembly, wherein the rear annular shaft engages the bearing to support the rotor blade assembly, is capable of movement in the axial direction with respect to the rotor shaft and is coupled to the rotor shaft in the axial and circumferential directions, the compression section including a forward bearing supported from the outer case of the engine and a forward annular shaft which is joined to a second rotor blade assembly, wherein the forward annular shaft engages the bearing to support the rotor blade assembly, is capable of movement in the axial direction with respect to the rotor shaft and is coupled to the rotor shaft in the axial and circumferential directions, the improvement which comprises the steps of:

uncoupling the low rotor shaft from the rear annular shaft;

uncoupling the low rotor shaft from the forward annular shaft;

separating the low rotor shaft and the engine by relative axial movement between the low rotor shaft and the annular shafts to remove the rotor shaft from the interior of the engine;

supporting the rotor blade assemblies from the outer case through the annular shafts after separating the rotor shaft and the annular shafts to avoid relative radial movement between the outer case and the rotor blade assembly.