US 11,939,925 B2
Descent operation for an aircraft parallel hybrid gas turbine engine propulsion system
Charles E. Lents, Amston, CT (US); Joseph B. Staubach, Colchester, CT (US); Larry W. Hardin, East Hartford, CT (US); and Jonathan Rheaume, West Hartford, CT (US)
Assigned to RTX Corporation, Farmington, CT (US)
Filed by Raytheon Technologies Corporation, Farmington, CT (US)
Filed on Jun. 15, 2022, as Appl. No. 17/840,715.
Application 17/840,715 is a division of application No. 15/200,149, filed on Jul. 1, 2016, granted, now 11,428,170.
Prior Publication US 2022/0349351 A1, Nov. 3, 2022
Int. Cl. F02C 7/36 (2006.01); B64D 27/10 (2006.01); B64D 27/24 (2006.01); B64D 31/06 (2006.01); F01D 15/10 (2006.01); F02C 6/14 (2006.01); F02C 9/50 (2006.01); B64D 27/02 (2006.01)
CPC F02C 7/36 (2013.01) [B64D 27/10 (2013.01); B64D 27/24 (2013.01); B64D 31/06 (2013.01); F01D 15/10 (2013.01); F02C 6/14 (2013.01); F02C 9/50 (2013.01); B64D 2027/026 (2013.01); F05D 2220/76 (2013.01); Y10S 903/905 (2013.01); Y10S 903/906 (2013.01)] 16 Claims
OG exemplary drawing
 
1. A method for operating a gas turbine engine comprising:
generating thrust at least in part by operating a gas turbine engine core at a maximum temperature during a first mode of operation; and
generating no thrust from said gas turbine engine core in a descent mode of operation; and
wherein the gas turbine engine has:
a core including a compressor section with a first compressor and a second compressor, a turbine section with a first turbine and a second turbine, and a primary flowpath fluidly connecting the compressor section and the turbine section;
the first compressor is connected to the first turbine via a first shaft;
the second compressor is connected to the second turbine via a second shaft;
a motor connected to the first shaft such that rotational energy generated by the motor is translated to the first shaft;
wherein the gas turbine engine includes a takeoff mode of operation, a top of climb mode of operation, and at least one additional mode of operation;
a controller configured to control the mode of operation of the gas turbine engine; and wherein the at least one additional mode of operation includes a cruise mode of operation and controlling by the controller the gas turbine engine such that a turbine inlet temperature of the second turbine is at a maximum temperature for the top of climb mode of operations while said engine is in said cruise mode of operation, and wherein the maximum turbine inlet temperature corresponds to a maximum thrust output of the core and the maximum thrust output of the core is less than an aircraft thrust requirement on the gas turbine engine in at least one of the takeoff mode of operations and the top of climb mode of operations.