US 12,234,791 B2
Geared turbomachine fan and compressor rotation
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 Jan. 30, 2023, as Appl. No. 18/161,340.
Application 16/812,636 is a division of application No. 15/411,459, filed on Jan. 20, 2017, granted, now 10,584,660, issued on Mar. 10, 2020.
Application 18/161,340 is a continuation of application No. 16/812,636, filed on Mar. 9, 2020, granted, now 11,566,587.
Application 15/411,459 is a continuation of application No. 13/356,940, filed on Jan. 24, 2012, abandoned.
Prior Publication US 2023/0167787 A1, Jun. 1, 2023
Int. Cl. F02K 3/06 (2006.01); F01D 25/16 (2006.01); F02C 7/36 (2006.01); F04D 29/52 (2006.01)
CPC F02K 3/06 (2013.01) [F01D 25/168 (2013.01); F02C 7/36 (2013.01); F04D 29/522 (2013.01); F05D 2220/36 (2013.01); F05D 2260/40311 (2013.01)] 22 Claims
OG exemplary drawing
 
1. A gas turbine engine comprising:
a propulsor section including a propulsor rotor and at least one propulsor blade;
a compressor section including a compressor inlet having an entrance at a splitter, a first compressor and a second compressor, wherein the first compressor includes a plurality of stages, and the second compressor has a pressure ratio greater than 20, wherein the at least one propulsor blade is forward of the splitter relative to an engine longitudinal axis;
a geared architecture having an input, an output, and a gear reduction ratio of greater than 2.3; and
a turbine section including a first turbine and a second turbine, wherein the first turbine is connected to the second compressor, wherein the geared architecture interconnects the second turbine with the first compressor and the propulsor rotor, and wherein the second turbine includes an inlet, an outlet and a pressure ratio greater than 5, and the pressure ratio is pressure measured prior to the inlet as related to pressure at the outlet;
wherein the first compressor includes a first compressor rotor that rotates together with the propulsor rotor at a common speed and in the same direction with the output of the geared architecture in operation.