US 11,859,538 B2
Geared turbofan engine with targeted modular efficiency
Frederick M. Schwarz, Glastonbury, CT (US)
Assigned to RTX CORPORATION, Farmington, CT (US)
Filed by RTX CORPORATION, Farmington, CT (US)
Filed on Jan. 13, 2023, as Appl. No. 18/096,872.
Application 18/096,872 is a continuation of application No. 17/737,179, filed on May 5, 2022, granted, now 11,585,268.
Application 17/737,179 is a continuation of application No. 17/038,608, filed on Sep. 30, 2020, granted, now 11,371,427, issued on Jun. 28, 2022.
Application 17/038,608 is a continuation of application No. 16/531,704, filed on Aug. 5, 2019, granted, now 10,823,052, issued on Nov. 3, 2020.
Application 16/531,704 is a continuation of application No. 14/651,923, granted, now 10,371,047, issued on Aug. 6, 2019, previously published as PCT/US2014/057127, filed on Sep. 24, 2014.
Claims priority of provisional application 61/891,475, filed on Oct. 16, 2013.
Prior Publication US 2023/0160338 A1, May 25, 2023
This patent is subject to a terminal disclaimer.
Int. Cl. F02C 3/107 (2006.01); F01D 5/14 (2006.01); F02K 3/06 (2006.01)
CPC F02C 3/107 (2013.01) [F01D 5/142 (2013.01); F02K 3/06 (2013.01); F05D 2220/327 (2013.01); F05D 2220/36 (2013.01); F05D 2260/40311 (2013.01); Y02T 50/60 (2013.01)] 8 Claims
OG exemplary drawing
 
1. A turbine engine comprising:
a fan section including a plurality of fan blades supported on a hub;
a speed change system coupled to the hub with a gear ratio greater than 2.6;
a first compression section including a last blade trailing edge tip length that is greater than 67% of the radial length of a first stage leading edge of the first compression section;
an eight stage second compression section including a last blade with a trailing edge tip that includes a radial length that is greater than 57% of a radial length of the first stage leading edge of the second compression section;
a turbine section including a fan drive turbine section coupled to the speed change system and at least two turbine stages forward of a first turbine blade of the fan drive turbine section; and
a mid-turbine frame disposed within the turbine section for guiding core flow between turbine stages, the mid-turbine frame supporting a bearing system for one of the fan drive turbine and the at least two turbine stages.