US2013232768A1PendingUtilityA1

Turbine engine case mount and dismount

45
Individually held — no corporate assignee on recordPriority: Mar 12, 2012Filed: Mar 12, 2012Published: Sep 12, 2013
Est. expiryMar 12, 2032(~5.6 yrs left)· nominal 20-yr term from priority
Inventors:Gabriel L. SuciuIoannis AlvanosBrian D. Merry
B64D 27/406B64D 27/404F05D 2220/323F05D 2230/60F05D 2240/90Y10T29/49947B64D 27/10F02C 7/20Y02T50/40
45
PatentIndex Score
0
Cited by
0
References
0
Claims

Abstract

A method for mounting a gas turbine engine having a compressor section, a combustor section, a turbine section, a pylon and a rear mount bracket, includes positioning the mounting bracket between the gas turbine engine and the pylon. The mounting bracket is connected to the turbine case reacting a least a vertical load, a side load, a thrust load, and a torque load from the gas turbine engine through the mounting bracket. The mounting bracket is attached to the pylon reacting the same loads from the gas turbine engine.

Claims

exact text as granted — not AI-modified
1 . A method of mounting a gas turbine engine to a pylon, the method comprising:
 attaching a mount bracket to the turbine exhaust case;   attaching a distal end of the mount bracket to the pylon with a single pin.   
     
     
         2 . The method of  claim 1  wherein attaching the mount bracket to the turbine exhaust case comprises:
 attaching a first leg of a yoke of the mounting bracket to a first engine pad. 
 
     
     
         3 . The method of  claim 2  wherein attaching the mount bracket to the turbine exhaust case comprises:
 attaching a second leg of the yoke of the mounting bracket to a second engine pad. 
 
     
     
         4 . The method of  claim 3  wherein attaching the second leg comprises securing a bolt to allow radial movement of the turbine exhaust case relative to the second leg through an aperture of the second leg. 
     
     
         5 . The method of  claim 4  wherein attaching the first leg comprises securing only a bolt through an aperture of the first leg. 
     
     
         6 . The method of  claim 4  wherein the aperture of the first leg and the aperture of the second leg each contain a bearing. 
     
     
         7 . The method of  claim 1  where the distal end of the mount bracket contains a spherical bearing. 
     
     
         8 . A method for mounting a gas turbine engine having a compressor section, a combustor section, a turbine section, a pylon and a rear mount bracket, the method comprising:
 positioning the mounting bracket between the gas turbine engine and the pylon;   connecting the mounting bracket to the turbine case reacting a least a vertical load, a side load, a thrust load, and a torque load from the gas turbine engine through the mounting bracket; and   connecting the mounting bracket to the pylon reacting at the vertical, side, thrust, and torque loads from the gas turbine engine to the pylon.   
     
     
         9 . The method of  claim 8  wherein connecting the mounting bracket to the pylon is done with a connection comprising a single pin passing through apertures in the pylon and mounting bracket. 
     
     
         10 . The method of  claim 9  wherein connecting the mount bracket to the turbine case comprises:
 attaching a first leg of a yoke of the mounting bracket to a first engine pad. 
 
     
     
         11 . The method of  claim 10  wherein connecting the mount bracket to the turbine case comprises:
 attaching a second leg of the yoke of the mounting bracket to a second engine pad. 
 
     
     
         12 . The method of  claim 11  wherein attaching the second leg comprises securing a bolt to allow radial movement of the turbine exhaust case relative to the second leg through an aperture of the second leg. 
     
     
         13 . The method of  claim 12  wherein attaching the first leg comprises radially securing a bolt through an aperture of the first leg providing the reacting of the side load. 
     
     
         14 . The method of  claim 13  wherein the aperture of the first leg and the aperture of the second leg each contain a bearing providing the reacting of the torque, thrust, and vertical loads. 
     
     
         15 . The method of  claim 13  where the mount bracket contains a spherical bearing to providing the reacting of the verticle load. 
     
     
         16 . A method of mounting a gas turbine engine to a pylon, the method comprising:
 attaching a mounting bracket to a pylon with a single pin connection that reacts a verticle load of the engine; and   attaching a yoke of the mounting bracket about a case of the gas turbine engine.   
     
     
         17 . The method of  claim 16  wherein the yoke has a first leg and a second leg, the first leg includes a first attachment fastener aperture and the second leg includes a second attachment fastener aperture, the first attachment fastener aperture and said second attachment fastener aperture defined along an attachment fastener axis which extends radially inward to intersect an engine axis. 
     
     
         18 . The method of  claim 17 , wherein the first leg and the second leg react vertical loads, torque, and thrust loads. 
     
     
         19 . The method of  claim 18 , wherein only the first leg also reacts a side load. 
     
     
         20 . The method of  claim 16  further comprising:
 (b) providing at least one spherical bearing in the mounting bracket.

Join the waitlist — get patent alerts

Track US2013232768A1 — get alerts on status changes and closely related new filings.

We store only your email — no account needed. See our privacy policy.