Lisa I. Brilliant, Middletown, CT (US); Becky E. Rose, Colchester, CT (US); Yuan Dong, Glastonbury, CT (US); and Stanley J. Balamucki, The Villages, FL (US)
Assigned to RTX CORPORATION, Farmington, CT (US)
Filed by RTX CORPORATION, Farmington, CT (US)
Filed on Jun. 9, 2023, as Appl. No. 18/207,805.
Application 18/207,805 is a continuation of application No. 17/892,529, filed on Aug. 22, 2022, granted, now 11,725,670.
Application 17/892,529 is a continuation of application No. 16/715,528, filed on Dec. 16, 2019, granted, now 11,428,242, issued on Aug. 30, 2022.
Application 16/715,528 is a continuation of application No. 15/084,643, filed on Mar. 30, 2016, granted, now 10,544,802, issued on Jan. 28, 2020.
Application 15/084,643 is a continuation of application No. 13/409,305, filed on Mar. 1, 2012, abandoned.
Claims priority of provisional application 61/593,001, filed on Jan. 31, 2012.
Prior Publication US 2023/0332622 A1, Oct. 19, 2023
1. A gas turbine engine comprising: a propulsor section including a propulsor that delivers flow to a core flowpath; a compressor section including a first compressor and a second compressor axially aft of the first compressor relative to an engine longitudinal axis, wherein the first compressor includes a plurality of stages distributed along the engine longitudinal axis, the second compressor includes a greater number of stages than the first compressor, and the core flowpath passes through the first compressor; a geared architecture including an epicyclic gear train; a turbine section including a first turbine and a second turbine, wherein the first turbine includes two stages, the second turbine includes a greater number of stages than the first turbine, the first turbine drives the second compressor, and the second turbine drives the propulsor section through the geared architecture; and wherein the core flowpath in the first compressor has an inner diameter and an outer diameter relative to the engine longitudinal axis, the outer diameter has a slope angle that is at least 5 degrees and no more than 15 degrees relative to the engine longitudinal axis such that the outer diameter of the core flow path slopes toward the engine longitudinal axis along a fluid flow direction of the core flowpath, and the inner diameter of the core flowpath increases through the first compressor along the fluid flow direction of the core flowpath, wherein a forwardmost one of the rotor blades of the first compressor establishing the outer diameter is axially aft of the geared architecture relative to the engine longitudinal axis.
