Engine modularity

• US 4,744,214 A
• Filed: 06/29/1987
• Issued: 05/17/1988
• Est. Priority Date: 06/29/1987
• 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: Monsarrat, William G., Brodell, Robert F.
• Primary Examiner(s): Casaregola, Louis J.
• Assistant Examiner(s): Stout, Donald E.
• Application Number:
  US07/067,339
• Time in Patent Office: 323 Days
• Field of Search: 60/226.1, 60/39.161, 60/39.31, 60/39.32, 416/171, 416/170 R, 415/143, 415/122 R
• US Class Current: 60/226.1
• CPC Class Codes: F01D 5/026 Shaft to shaft connections
• CPC Class Codes: F02K 3/06 with front fan

Abstract

The low pressure compressor and fan together with the intermediate case are removable as a unit from the core engine by removal of the nose cone and a stub shaft at the front of the low pressure turbine shaft and at the ID of the fan hub (50) to provide access to attachment bolts at the inner portion of the intermediate case which holds the bearing for the high pressure rotor in position within the intermediate case after assembly of the engine.

Claims

1. In a turbine engine:

a low pressure compressor casing,

a low pressure rotor within the casing,

an intermediate stout attached to the downstream end of said casing and having a bearing support structure extending forwardly from the strut within the casing and rotor,

a bearing on said support for said low pressure rotor,

a high pressure compressor rotor downstream of the strut,

a bearing structure at the inner portion of the strut to support the high pressure rotor within this strut, said bearing having an axially slidable connection with the strut,

a low pressure shaft within the high pressure compressor rotor and extending forwardly therefrom,

a stub shaft having a splined connection with the low pressure shaft and with the low pressure rotor adjacent to its forward end to provide for axial assembly of the stub shaft within the engine,

means for removably securing said stub shaft to said low pressure shaft at the forward end of said low pressure shaft, said securing means being accessible within the stub shaft, and

securing bolts to hold said bearing structure axially within the strut, said bolts being accessible through the low pressure rotor when the stub shaft is removed from within the compressor.

2. A turbine engine as in claim 1 in which said bearing structure has a cylindrical outer surface and said intermediate strut has an inner cylindrical surface cooperating therewith for axial sliding movement of the strut over the bearing structure and cooperating flanges on said structure and said strut to receive the bolts for securing the bearing structure within the strut.

3. A turbine engine as in claim 1 in which the securing means is a threaded ring engaging with threads on the inner low pressure shaft with said ring being shouldered to hold the stub shaft against the end of the low pressure shaft.

4. A turbine engine as in claim 1 in which the low pressure compressor rotor includes a fan at its forward end and this fan has a supporting disk to which the rest of the low compressor rotor is secured and this disk has internal splines thereon to engage with cooperating splines on the stub shaft.

5. A turbine engine as in claim 4 in which there is a threaded ring on the forward end of the fan disk to hold the stub shaft in position therein.

6. A turbine engine as in claim 4 in which the cooperating splines on the stub shaft and the low pressure shaft are internal splines on the stub shaft and external splines on the low pressure shaft and the cooperating splines at the forward end of the stub shaft are external on the stub shaft and internal on the low pressure compressor rotor.

7. A turbine engine as in claim 4 in which the cooperating splines on the stub shaft and the low pressure compressor rotor are internal on the rotor and external on the stub shaft.

8. A turbine engine as in claim 7 in which there is a clamping ring at the end of the fan disk and engaging the end of the stub shaft to hold the fan disk on the stub shaft.