US 11,731,773 B2
Engine mount system for a gas turbine engine
Gabriel L. Suciu, Glastonbury, CT (US); Brian D. Merry, Andover, CT (US); Christopher M. Dye, San Diego, CA (US); Steven B. Johnson, Marlborough, CT (US); and Frederick M. Schwarz, Glastonbury, CT (US)
Assigned to RAYTHEON TECHNOLOGIES CORPORATION, Farmington, CT (US)
Filed by RAYTHEON TECHNOLOGIES CORPORATION, Farmington, CT (US)
Filed on Aug. 6, 2021, as Appl. No. 17/395,553.
Application 17/395,553 is a continuation of application No. 16/405,149, filed on May 7, 2019, granted, now 11,286,883.
Application 16/405,149 is a continuation of application No. 15/173,288, filed on Jun. 3, 2016, granted, now 10,451,004, issued on Oct. 22, 2019.
Application 15/173,288 is a continuation of application No. 14/755,221, filed on Jun. 30, 2015, abandoned.
Application 14/755,221 is a continuation of application No. 14/190,429, filed on Feb. 26, 2014, abandoned.
Application 14/190,429 is a continuation in part of application No. 13/340,988, filed on Dec. 30, 2011, granted, now 8,800,914, issued on Aug. 12, 2014.
Application 13/340,988 is a continuation in part of application No. 12/131,876, filed on Jun. 2, 2008, granted, now 8,128,021, issued on Mar. 6, 2012.
Prior Publication US 2021/0372349 A1, Dec. 2, 2021
Int. Cl. B64D 27/26 (2006.01); F01D 25/28 (2006.01); F02C 7/20 (2006.01); F02K 3/06 (2006.01); F02C 9/20 (2006.01); F02C 9/18 (2006.01); F02C 7/36 (2006.01); F02C 3/107 (2006.01); F01D 5/06 (2006.01); F01D 9/02 (2006.01); F01D 15/12 (2006.01); F01D 25/24 (2006.01); F02K 1/15 (2006.01)
CPC B64D 27/26 (2013.01) [F01D 5/06 (2013.01); F01D 9/02 (2013.01); F01D 15/12 (2013.01); F01D 25/24 (2013.01); F01D 25/28 (2013.01); F02C 3/107 (2013.01); F02C 7/20 (2013.01); F02C 7/36 (2013.01); F02C 9/18 (2013.01); F02C 9/20 (2013.01); F02K 1/15 (2013.01); F02K 3/06 (2013.01); B64D 2027/266 (2013.01); B64D 2027/268 (2013.01); F05D 2220/32 (2013.01); F05D 2220/36 (2013.01); F05D 2260/4031 (2013.01); F05D 2260/40311 (2013.01); F05D 2270/42 (2013.01)] 30 Claims
OG exemplary drawing
 
1. A gas turbine engine comprising:
a propulsor section including a rotor having a plurality of blades;
an epicycle gear train;
a low spool and a high spool rotatable about an engine axis of rotation, the low spool including a low pressure compressor and a low pressure turbine, the high spool including a high pressure turbine that drives a high pressure compressor, and wherein the low pressure turbine drives the propulsor section through the gear train;
a combustor between the high pressure compressor and the high pressure turbine;
a static structure that supports a bearing system upon which the low pressure and high pressure turbines, the low pressure and high pressure compressors and the rotor rotate, wherein the static structure includes a plurality of cases, and the plurality of cases includes a first case and a second case positioned aft of the first case with respect to the engine axis of rotation; and
a mount system including a forward mount and an aft mount arranged in a plane containing the engine axis of rotation, wherein the forward mount is secured to the first case, the aft mount is secured to the second case, and the aft mount comprises:
a rear mount platform mountable to an aircraft structure, wherein the aft mount reacts at least a vertical load and a side load in operation;
a whiffle tree assembly including a whiffle link supporting a first sliding ball joint and a second sliding ball joint;
a first A-arm mounted to the rear mount platform through a first ball joint and the whiffle tree assembly through the first sliding ball joint; and
a second A-arm mounted to the rear mount platform through a second ball joint and the whiffle tree assembly through the second sliding ball joint.