Gas turbine engine

A gas turbine engine comprising:

• a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a high pressure compressor defining a high pressure compressor exit area (AHPCExit) in square inches and the turbine section having a drive turbine defining a drive turbine exit area (ADTExit) in square inches, the turbomachine further comprising a drive turbine shaft coupled to the drive turbine and defining an overall pressure ratio greater than 14:1 and less than or equal to 22:1;
• wherein the gas turbine engine defines a maximum exhaust gas temperature (EGT) greater than 600 degrees Celsius and less than 1000 degrees Celsius, an output power of at least 550 horsepower and up to 2,000 horsepower when operated at a rated speed, a maximum drive turbine shaft torque (TOUT) in Newton meters, and a corrected specific power (CSP) in Newtons squared times degrees Celsius over meters squared, wherein CSP is greater than 3.3 and less than 101 and is determined as follows:
• (
• T
• OUT
• A
• DTExit
• )
• 2
• *
• EGT
• A
• HPCExit
• *
• 1
• ⁢
• 0
• -
• 1
• ⁢
• 1
• ;
• and
• wherein the compressor section comprises a centrifugal compressor stage having an impeller and a deswirler assembly.

A method of operating a gas turbine engine, comprising:

• operating the gas turbine engine at a takeoff power level, wherein operating the gas turbine engine at the takeoff power level comprises driving a propeller of a propeller assembly across a propeller shaft of the propeller assembly, the gas turbine engine further comprising a turbomachine with a high pressure compressor defining a high pressure compressor exit area (AHPCExit) in square inches and a drive turbine defining a drive turbine exit area (ADTExit) in square inches, the gas turbine engine defining a maximum exhaust gas temperature (EGT) in degrees Celsius, a maximum drive turbine shaft torque (TOUT) in Newton meters, and a corrected specific power in Newtons squared times degrees Celsius over meters squared;
• wherein the corrected specific power (CSP) is determined as follows:
• (
• T
• OUT
• A
• DTExit
• )
• 2
• *
• EGT
• A
• HPCExit
• *
• 1
• ⁢
• 0
• -
• 1
• ⁢
• 1
• ;
• wherein CSP is greater than 0.0001194×EGT2−0.103×EGT+22.14 and less than 0.0003294×EGT2−0.306×EGT+77.91;
• wherein EGT is greater than 525 degrees Celsius and less than 1250 degrees Celsius;
• and
• wherein the gas turbine engine comprises a centrifugal compressor stage having an impeller and a deswirler assembly.