US 12,006,876 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 Nov. 16, 2021, as Appl. No. 17/527,542.
Application 17/527,542 is a continuation of application No. 16/436,569, filed on Jun. 10, 2019, granted, now 11,203,982.
Application 16/436,569 is a continuation of application No. 14/888,154, granted, now 10,316,758, issued on Jun. 11, 2019, previously published as PCT/US2014/036475, filed on May 2, 2014.
Claims priority of provisional application 61/821,387, filed on May 9, 2013.
Prior Publication US 2022/0074350 A1, Mar. 10, 2022
This patent is subject to a terminal disclaimer.
Int. Cl. F02C 7/36 (2006.01); F02K 3/06 (2006.01)
CPC F02C 7/36 (2013.01) [F02K 3/06 (2013.01); F05D 2260/40311 (2013.01)] 19 Claims
OG exemplary drawing
 
1. A gas turbine engine comprising:
a propulsor section;
a compressor section including a compressor entrance passage including an inlet disposed at an inlet diameter and an outlet to the compressor disposed at an outlet diameter;
a combustor receiving airflow from the compressor section and generating a high-energy flow;
a turbine section driven by the high-energy flow;
a geared architecture configured to be driven by the turbine section for driving the propulsor section at a speed different than the turbine section, wherein a geared architecture power transfer parameter (PTP) is defined as power transferred through the geared architecture divided by gear volume multiplied by a gear reduction ratio and is between 219 and 328.