US Patent Application 18107126. GAS TURBINE ENGINE WITH POWER DENSITY RANGE simplified abstract
Contents
GAS TURBINE ENGINE WITH POWER DENSITY RANGE
Organization Name
Raytheon Technologies Corporation
Inventor(s)
Frederick M. Schwarz of Glastonbury CT (US)
Daniel Bernard Kupratis of Wallingford CT (US)
GAS TURBINE ENGINE WITH POWER DENSITY RANGE - A simplified explanation of the abstract
This abstract first appeared for US patent application 18107126 titled 'GAS TURBINE ENGINE WITH POWER DENSITY RANGE
Simplified Explanation
The abstract describes a gas turbine engine with specific components and a power density ratio.
- Gas turbine engine with a propulsor section, compressor section, geared architecture, and turbine section.
- Compressor section includes a first and second compressor.
- Turbine section includes a first turbine and a drive turbine.
- Power density ratio of the engine is between 4.75 and 5.5 lbf/in.
- Power density ratio is calculated by dividing the thrust provided by the engine by the volume of the turbine section.
Original Abstract Submitted
A gas turbine engine includes a propulsor section including a propulsor, a compressor section including a first compressor and a second compressor, a geared architecture, a turbine section including a first turbine and a drive turbine, and a power density of greater than or equal to 4.75 and less than or equal to 5.5 lbf/in, wherein the power density is a ratio of a thrust provided by the engine to a volume of the turbine section.
