US 12,085,025 B2
Gas turbine engine compressor arrangement
Karl L. Hasel, Manchester, CT (US); Joseph B. Staubach, Colchester, CT (US); Brian D. Merry, Andover, CT (US); Gabriel L. Suciu, Glastonbury, CT (US); and Christopher M. Dye, San Diego, CA (US)
Assigned to RTX CORPORATION, Farmington, CT (US)
Filed by RTX CORPORATION, Farmington, CT (US)
Filed on Nov. 7, 2023, as Appl. No. 18/387,527.
Application 18/387,527 is a continuation of application No. 17/060,171, filed on Oct. 1, 2020, granted, now 11,846,238.
Application 17/060,171 is a continuation of application No. 15/184,253, filed on Jun. 16, 2016, granted, now 10,830,152, issued on Nov. 10, 2020.
Application 15/184,253 is a continuation of application No. 14/179,640, filed on Feb. 13, 2014, abandoned.
Application 14/179,640 is a continuation in part of application No. 13/869,057, filed on Apr. 24, 2013, granted, now 9,121,367, issued on Sep. 1, 2015.
Application 13/869,057 is a continuation of application No. 13/590,273, filed on Aug. 21, 2012, granted, now 8,449,247, issued on May 28, 2013.
Application 13/590,273 is a continuation of application No. 13/418,457, filed on Mar. 13, 2012, granted, now 8,277,174, issued on Oct. 2, 2012.
Application 13/418,457 is a continuation in part of application No. 13/337,354, filed on Dec. 27, 2011, granted, now 8,337,147, issued on Dec. 25, 2012.
Application 13/337,354 is a continuation in part of application No. 13/294,492, filed on Nov. 11, 2011, granted, now 8,596,965, issued on Dec. 3, 2013.
Application 13/294,492 is a continuation of application No. 11/858,988, filed on Sep. 21, 2007, granted, now 8,075,261, issued on Dec. 13, 2011.
Claims priority of provisional application 61/604,646, filed on Feb. 29, 2012.
Prior Publication US 2024/0068411 A1, Feb. 29, 2024
This patent is subject to a terminal disclaimer.
Int. Cl. F02C 7/36 (2006.01); F02C 3/04 (2006.01); F02C 3/06 (2006.01); F02C 3/107 (2006.01); F02K 3/02 (2006.01); F02K 3/06 (2006.01)
CPC F02C 7/36 (2013.01) [F02C 3/04 (2013.01); F02C 3/06 (2013.01); F02C 3/107 (2013.01); F02K 3/025 (2013.01); F02K 3/06 (2013.01); F05D 2220/32 (2013.01); F05D 2220/323 (2013.01); F05D 2260/4031 (2013.01); F05D 2260/40311 (2013.01)] 30 Claims
OG exemplary drawing
 
1. A gas turbine engine comprising:
a propulsor section including a propulsor having at least one blade;
a core engine including a compressor section and a turbine section;
a gear arrangement that drives the propulsor, the gear arrangement including an epicyclic gear train having a sun gear, a ring gear, and a plurality of intermediate gears arranged circumferentially about the sun gear and intermeshing with the sun gear and the ring gear, and the gear arrangement defining a gear reduction ratio of greater than 2.3:1;
a lubrication system and a compressed air system in fluid communication with the gear arrangement;
wherein the compressor section includes a first compressor section and a second compressor section downstream of the first compressor section;
wherein the turbine section includes a first turbine having two stages and a second turbine that drives an input of the epicylic gear train, the second turbine includes an inlet, an outlet, and a turbine pressure ratio greater than 5:1, wherein the turbine pressure ratio is a ratio of a pressure measured prior to the inlet as related to a pressure at the outlet prior to any exhaust nozzle, wherein the first compressor section has a greater number of stages than the first turbine, and wherein the second compressor section has a greater number of stages than a total number of stages of the turbine section;
wherein an overall pressure ratio is:
provided by the combination of a pressure ratio across the first compressor section and a pressure ratio across the second compressor section; and
greater than 40;
wherein the pressure ratio across the second compressor section is between 7 and 15; and
wherein the pressure ratio across the first compressor section is between 4 and 8.