US 11,952,947 B2
Hybrid electric fan with stall free low pressure compressor
Daniel Bernard Kupratis, Wallingford, CT (US); Christopher J. Hanlon, Sturbridge, MA (US); and William G Sheridan, Southington, CT (US)
Assigned to RTX CORPORATION, Farmington, CT (US)
Filed by Raytheon Technologies Corporation, Farmington, CT (US)
Filed on Oct. 4, 2021, as Appl. No. 17/493,002.
Application 17/493,002 is a continuation of application No. 15/980,870, filed on May 16, 2018, granted, now 11,168,616.
Prior Publication US 2022/0025823 A1, Jan. 27, 2022
This patent is subject to a terminal disclaimer.
Int. Cl. F02C 7/36 (2006.01); F02C 6/00 (2006.01); F02C 9/00 (2006.01); F02K 3/06 (2006.01); F16H 1/28 (2006.01); H02K 7/116 (2006.01); H02K 7/14 (2006.01); H02K 7/18 (2006.01)
CPC F02C 7/36 (2013.01) [F02C 6/00 (2013.01); F02C 9/00 (2013.01); F02K 3/06 (2013.01); F16H 1/28 (2013.01); H02K 7/116 (2013.01); H02K 7/14 (2013.01); H02K 7/1823 (2013.01); F05D 2220/323 (2013.01); F05D 2220/70 (2013.01); F05D 2260/40311 (2013.01); F05D 2270/02 (2013.01); F05D 2270/051 (2013.01); F05D 2270/101 (2013.01); F05D 2270/20 (2013.01)] 16 Claims
OG exemplary drawing
 
1. A gas turbine engine comprising:
a fan section including a fan shaft and a plurality of fan blades;
a propulsor electric motor assembly coupled to the fan shaft and configured to provide a first drive input for driving the fan blades about an axis;
a turbine section;
a geared architecture driven by the turbine section and coupled to the fan shaft to provide a second drive input for driving the fan blades about the axis, the geared architecture defining a speed reduction between a speed of the turbine section and the second drive input, wherein the geared architecture includes a sun gear driven by a shaft of the turbine section, a plurality of intermediate gears supported in a carrier and circumscribed by a ring gear and by a driven gear engaged in contact with the carrier, wherein the sun gear is driven by the shaft of the turbine section and in turn drives the intermediate gears that drive the ring gear and the ring gear is coupled to the fan shaft to provide the second drive input; and
a geared architecture electric motor assembly coupled to the driven gear of the geared architecture and configured to rotate the geared architecture about the axis relative to a fixed structure to adjust the speed reduction and control a speed of the fan blades provided by a combination of the first drive input from the propulsor electric motor assembly and the second drive input from the turbine section, wherein the geared architecture electric motor assembly is configured to rotate the geared architecture in a first direction to increase the speed reduction and in a second direction opposite the first direction to decrease the speed reduction, the geared architecture electric motor assembly comprises a first electric motor configured to drive a first drive gear engaged in contact with the driven gear to rotate the driven gear in the first direction and a second electric motor configured to a second drive gear engaged in contact with the driven gear to rotate the driven gear in the second direction.