US 12,247,493 B2
Gas turbine engine front section
Frederick M. Schwarz, Glastonbury, CT (US); and William G. Sheridan, Southington, CT (US)
Assigned to RTX CORPORATION, Farmington, CT (US)
Filed by RTX CORPORATION, Farmington, CT (US)
Filed on Oct. 19, 2022, as Appl. No. 17/969,179.
Application 17/969,179 is a continuation of application No. 17/337,658, filed on Jun. 3, 2021, granted, now 11,506,084.
Application 17/337,658 is a continuation of application No. 15/007,263, filed on Jan. 27, 2016, granted, now 11,053,816, issued on Jul. 6, 2021.
Application 15/007,263 is a continuation of application No. 14/785,872, granted, now 10,287,917, issued on May 14, 2019, previously published as PCT/US2014/035821, filed on Apr. 29, 2014.
Claims priority of provisional application 61/821,371, filed on May 9, 2013.
Prior Publication US 2023/0042974 A1, Feb. 9, 2023
This patent is subject to a terminal disclaimer.
Int. Cl. F02C 7/36 (2006.01); F01D 5/02 (2006.01); F01D 5/12 (2006.01); F01D 17/10 (2006.01); F01D 25/24 (2006.01); F02C 3/107 (2006.01); F02K 3/06 (2006.01); F04D 29/32 (2006.01); F16H 1/28 (2006.01)
CPC F01D 25/24 (2013.01) [F01D 5/02 (2013.01); F01D 5/12 (2013.01); F01D 17/105 (2013.01); F02C 3/107 (2013.01); F02K 3/06 (2013.01); F04D 29/321 (2013.01); F16H 1/28 (2013.01); F02C 7/36 (2013.01); F05D 2220/32 (2013.01); F05D 2220/36 (2013.01); F05D 2230/60 (2013.01); F05D 2240/24 (2013.01); F05D 2250/51 (2013.01); F05D 2260/40311 (2013.01)] 30 Claims
OG exemplary drawing
 
1. A gas turbine engine comprising:
a propulsor section including a propulsor hub, the hub including a hub diameter supporting a plurality of propulsor blades;
a compressor section including a first compressor and a second compressor, and each of the first and second compressors including a plurality of stages;
a turbine section including a first turbine and a second turbine, wherein the second turbine drives the second compressor, and each of the first and second turbines includes a plurality of stages;
a geared architecture that interconnects the first turbine and the propulsor hub, the geared architecture including a gear volume between 1318 in3 and 1977 in3; and
a compressor inlet passage disposed annularly about the geared architecture, the compressor inlet passage coupling the propulsor section and the compressor section, the compressor inlet passage including an inlet disposed at an inlet diameter and an outlet disposed at an outlet diameter, the inlet adjacent to the propulsor section, the outlet adjacent to the compressor section, and a ratio of the propulsor hub diameter to the inlet diameter being between 0.65 and 0.95.