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METHOD AND APPARATUS FOR DETERMINING AXIAL LOAD DURING ENGINE ASSEMBLY

IP.com Disclosure Number: IPCOM000248063D
Publication Date: 2016-Oct-21
Document File: 5 page(s) / 128K

Publishing Venue

The IP.com Prior Art Database

Abstract

The present disclosure is directed to a technology that provides a method and apparatus for determining the relationship between applied torque angle of the coupling nut and the axial load generated by the coupling nut during a High Pressure Turbine Rotor (HPTR) assembly. In this regard, the method provides for accurate prediction of the axial preload that is developed in a HPTR assembly.

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Page 01 of 5

METHOD AND APPARATUS FOR DETERMINING AXIAL LOAD DURING
ENGINE ASSEMBLY

[0001] The present disclosure is directed to a technology that provides a method and apparatus for determining the relationship between applied torque angle of the coupling nut and the axial load generated by the coupling nut during a High Pressure Turbine Rotor (HPTR) assembly. In this regard, the method provides for accurate prediction of the axial preload that is developed in a HPTR assembly.

BACKGROUND


[0002] Accurate prediction of the axial preload of an HPTR assembly is critical for safer operation of the rotating structure of an aircraft engine. One problem with conventional methods of engine assembly is that over-torqueing or under-torqueing can occur due to an incorrect axial load. Currently there are no established procedures to determine the axial load that is generated in the HPTR assembly for a given torque-angle. Therefore there is a need for an apparatus and method for accurately determining the relationship between the axial load generated in the HPTR assembly and the applied torque-angle.


[0003] Accordingly, the present disclosure is directed to an apparatus, or component, and a method for determining the relationship between the axial load generated in the HPTR assembly for an applied torque angle.

BRIEF DESCRIPTION OF THE DRAWINGS


[0004] The concept may be best understood by reference to the following description taken in conjunction with the accompanying drawing figures, in which:


[0005] FIG. 1 is a schematic cross-sectional view of a portion of a high pressure turbine rotor; and


[0006] FIG. 2 is a schematic diagram showing the process of using the load ring described herein.

ABSTRACT


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DETAILED DESCRIPTION OF THE CONCEPT


[0007] An engine such as an aircraft-type high bypass ratio gas turbine engine includes a HPTR. A portion of an exemplary HPTR is shown in FIG. 1 and includes a first stage disk (not shown) and a second stage disk 16. An interstage seal 118 separates the first stage disk from the second stage disk 16. The second stage disk 16 has a web 20 that extends radially outward from a bore
24. The web 20 terminates in an outer periphery consisting of a plurality of blade dovetail slots.


[0008] The second stage disk 16 also includes a conical rear arm 50 which engages the aft shaft
42. The second stage disk 16 is secured by a locking nut 60 which is threaded on the aft shaft 42 rearwardly of the arm 50. The locking nut 60 is configured to transfer a load to a spacer ring 44 such that the shaft 42 is in tension. It is this axial force that is determined during assembly by indirect methods such as torque angle.


[0009] A load ring 10 can be seen in FIG. 2 is provided as a test component to determine the actual axial force that is transmitted by the locking nut 60 to the spacer ring 44 and thus to the shaft 42. The load ring 10 includes two substantially concentric surfaces that share the axis of the load ring. The concentric sur...