Geared turbofan arrangement with core split power ratio
AssigneeRaytheon Technologies Corporation
InventorsDaniel Bernard Kupratis, Frederick M. Schwarz
Life of this patent
Estimating the term…
Abstract
A propulsor section includes a propulsor having a plurality of blades rotatable about an engine longitudinal axis. A compressor section includes a low pressure compressor and a high pressure compressor. A turbine section includes a low pressure turbine that drives the propulsor through an epicyclic gear arrangement, and includes a second turbine that drives the high pressure compressor. A power ratio is provided by the combination of a first power input of the low pressure compressor and a second power input of the high pressure compressor. The power ratio is defined by the second power input divided by the first power input. The power ratio is equal to, or greater than, 1.0 and less than, or equal to, 1.4.
Claims29
A gas turbine engine comprising:
- a propulsor section including a propulsor having a plurality of blades rotatable about an engine longitudinal axis, and the propulsor having a pressure ratio of less than 1.50 across the plurality of blades alone at cruise at 0.8 Mach and 35,000 feet;
- a compressor section including a low pressure compressor and a high pressure compressor;
- a turbine section including a low pressure turbine that drives the propulsor through an epicyclic gear arrangement, and including a second turbine that drives the high pressure compressor;
- and
- a power ratio provided by the combination of a first power input of the low pressure compressor and a second power input of the high pressure compressor, the power ratio defined by the second power input divided by the first power input, the power ratio being equal to, or greater than, 1.0 and less than, or equal to, 1.4.
Dependencies are inferred from the claim text.