US 11,982,238 B2
Fan and low pressure compressor geared to low speed spool of gas turbine engine
William G. Sheridan, Southington, CT (US); and Michael E. McCune, Colchester, CT (US)
Assigned to RTX CORPORATION, Farmington, CT (US)
Filed by RAYTHEON TECHNOLOGIES CORPORATION, Farmington, CT (US)
Filed on Aug. 4, 2022, as Appl. No. 17/881,399.
Application 17/881,399 is a division of application No. 17/236,850, filed on Apr. 21, 2021, granted, now 11,434,829.
Application 17/236,850 is a division of application No. 16/671,432, filed on Nov. 1, 2019, granted, now 11,015,533, issued on May 25, 2021.
Claims priority of provisional application 62/780,622, filed on Dec. 17, 2018.
Prior Publication US 2022/0372918 A1, Nov. 24, 2022
Int. Cl. F16H 1/28 (2006.01); F02C 7/36 (2006.01)
CPC F02C 7/36 (2013.01) [F16H 1/28 (2013.01); F05D 2220/36 (2013.01); F05D 2260/40311 (2013.01)] 8 Claims
OG exemplary drawing
 
1. A gas turbine engine comprising:
one of a fan or a prop;
a low pressure compressor;
a high speed spool mechanically connecting a high pressure turbine to a high pressure compressor;
a first epicyclic gear system;
a second epicyclic gear system; and
a low speed spool mechanically connecting a low pressure turbine to one of the fan or the prop via the first epicyclic gear system and to the low pressure compressor via the second epicyclic gear system, the low speed spool comprising a forward section defining a sun gear shaft for both the first epicyclic gear system and the second epicyclic gear system, wherein:
the low pressure compressor is immediately aft of the one of the fan or the prop,
the first epicyclic gear system, the second epicyclic gear system, the one of the fan or the prop, and the low pressure compressor are mounted to a common static support structure, and
the low speed spool is configured to drive the first epicyclic gear system and the second epicyclic gear system via the sun gear shaft.