Turbine engine bearing support

• US 6,428,269 B1
• Filed: 04/18/2001
• Issued: 08/06/2002
• Est. Priority Date: 04/18/2001
• Status: Expired due to Term

• Current Assignee: Raytheon Technologies Corporation d/b/a RTX (Rtx Corporation)
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: Coffin, James B., Boratgis, Ernest
• Primary Examiner(s): Lopez, F. Daniel
• Assistant Examiner(s): McCoy, Kimya N
• Application Number:
  US09/837,504
• Time in Patent Office: 475 Days
• Field of Search: 415/9, 415/229, 415/216.1, 415/174.4, 415/244.A, 411/5, 411/3, 411/2
• US Class Current: 415/9
• CPC Class Codes: F01D 21/045 special arrangements in stators or in rotors dealing with breaking-off of part of rotor
• CPC Class Codes: F05B 2260/3011 of the frangible or shear type

Abstract

A bearing support for a rotor of an aircraft turbine engine includes a frangible linkage designed to enable the engine to safely shut down despite the introduction of an excessive unbalance to the fan stage.

Claims

1. In an aircraft turbine engine comprising a rotor having a shaft which rotates about an axis of rotation R during balanced engine operation, a fan stage having at least two fan blades attached to the shaft, a bearing support structure for supporting the shaft for rotation, said bearing support structure comprising a front bearing and a rear bearing, and a first bearing support and a second bearing support for securely attaching the front bearing and the rear bearing to the aircraft turbine engines support structure, respectively, the improvement comprising the first bearing support includes a joint located at an axial distance “

a”

from the front bearing, the joint includes a frangible linkage wherein the joint is designed so as to substantially eliminate shear forces on the frangible linkage so that the frangible linkage is subjected to tensile force.

2. An aircraft turbine engine according to claim 1 wherein the joint includes a flange portion extending substantially parallel to the axis of rotation R for substantially eliminating shear force on the frangible coupling.

3. An aircraft turbine engine according to claim 1 wherein the joint comprises a first substantially L-shaped member having an upstanding portion and a base portion and a second upstanding member which rests on the base portion and abuts the upstanding portion, the upstanding portion and upstanding member having in line holes along an axis L which receives a bolt which forms the frangible linkage.

4. An aircraft turbine engine according to claim 3 wherein the axis L is substantially parallel to the axis of rotation R.

5. An aircraft turbine engine according to claim 3 wherein the base portion is substantially parallel to the axis L.

6. An aircraft turbine engine according to claim 3 wherein the bolt comprises a reduced diameter central portion between two larger diameter portions for forming the frangible link.

7. An aircraft turbine engine according to claim 1 wherein the front bearing is a roller bearing which substantially eliminates transfer of a variable moment from the rotor through the bearing and to the frangible linkage.

8. An aircraft turbine engine according to claim 6 wherein the first and second bearing supports, the front bearing, the rear bearing and the joint extend circumferentially about the shaft and the frangible linkage comprises a plurality of bolts.

9. In an aircraft turbine engine comprising a rotor having a shaft which rotates about an axis of rotation R during balanced engine operation, a fan stage having at least two fan blades attached to the shaft, a bearing support structure for supporting the shaft for rotation, said bearing support structure comprising a front bearing and a rear bearing, and a first bearing support and a second bearing support for securely attaching the front bearing and the rear bearing to the aircraft turbine engines support structure, respectively, a method for sensing predetermined excessive operating unbalance of the rotor and thereafter decrease load transfer to the aircraft turbine engine'"'"'s support structure comprising the steps of:

providing a device including a frangible linkage in the first bearing support at a distance “

a”

from the front bearing;

substantially eliminating the transfer of shear force to the frangible linkage while subjecting the linkage to tensile force; and

breaking the frangible linkage at a tensile force corresponding to the predetermined excessive operating unbalance of the rotor whereby support of the rotor by the front bearing is lost and the shaft rotational axis is changed so as to decrease load transfer to the engine'"'"'s support structure.