US 11,754,000 B2
High and low spool configuration for a gas turbine engine
Stephen G. Pixton, South Windsor, CT (US); Matthew R. Feulner, West Hartford, CT (US); Marc J. Muldoon, Marlborough, CT (US); and Xinwen Xiao, Katy, TX (US)
Assigned to RTX Corporation, Farmington, CT (US)
Filed by Raytheon Technologies Corporation, Farmington, CT (US)
Filed on Jul. 19, 2021, as Appl. No. 17/379,308.
Prior Publication US 2023/0022122 A1, Jan. 26, 2023
Int. Cl. F02C 7/36 (2006.01)
CPC F02C 7/36 (2013.01) [F05D 2220/36 (2013.01); F05D 2260/40311 (2013.01)] 12 Claims
OG exemplary drawing
 
1. A gas turbine engine comprising:
a fan section including a fan with fan blades, wherein said fan section drives air along a bypass flow path in a bypass duct;
a gear reduction in driving engagement with the fan and having a gear reduction ratio of greater than 3.0 and less than 4.0;
a low spool including a low pressure turbine driving a low pressure compressor and driving the gear reduction to drive the fan at a speed slower than the low pressure turbine, wherein the low pressure compressor is a four-stage low pressure compressor and the low pressure turbine is a three-stage low pressure turbine;
a high spool including a high pressure turbine driving a high pressure compressor, wherein the high pressure compressor is a nine-stage high pressure compressor and the high pressure turbine is a two-stage high pressure turbine; an exhaust gas exit temperature of greater than 900 degrees Fahrenheit and less than 1000 degrees Fahrenheit at maximum take-off;
wherein an overall pressure ratio provided by the pressure across the fan, the low pressure compressor, and the high pressure compressor is greater than 38 and less than 70 at cruise; and
wherein a pressure ratio of the low pressure turbine is greater than 7.5 and less than 12.5 at cruise.