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US 10,502,163 B2Granted
Geared turbofan arrangement with core split power ratio
AssigneeUnited Technologies Corporation
InventorsDaniel Bernard Kupratis, Frederick M. Schwarz
Life of this patent
Estimating the term…
Abstract
A gas turbine engine according to an example of the present disclosure includes, among other things, a fan section, and a compressor section including at least a first compressor section and a second compressor section. A power ratio is provided by the combination of the first compressor section and the second compressor section. A method of design a gas turbine engine is also disclosed.
Claims30
A gas turbine engine comprising:
- a fan section including a plurality of fan blades;
- a compressor section, including at least a first compressor section and a second compressor section;
- a turbine section including at least one turbine to drive said second compressor section and a fan drive turbine to drive at least an epicyclic gear arrangement to drive said fan section and said first compressor section, said turbine section including at least two turbine stages upstream of said fan drive turbine;
- and
- wherein a power ratio is provided by the combination of said first compressor section and said second compressor section, with said power ratio being provided by a second power input to said second compressor section divided by a first power input to said first compressor section, said power ratio being equal to, or greater than, 1.0 and less than, or equal to, 1.4.
2 more elements
A gas turbine engine comprising:
- a fan section including a plurality of fan blades;
- a compressor section, including at least a first compressor section and a second compressor section, said first compressor section including 3 or more stages and said second compressor section including 6 or more stages;
- a turbine section including at least one turbine to drive said second compressor section and a fan drive turbine to drive at least a gear arrangement to drive said fan section, said turbine section including at least 2 turbine stages upstream of said fan drive turbine;
- and
- wherein a power ratio is provided by the combination of said first compressor section and said second compressor section, with said power ratio being provided by a second power input to said second compressor section divided by a first power input to said first compressor section, said power ratio being equal to or greater than 1.0;
- and
- wherein an overall pressure ratio is provided by the combination of said first compressor section, said second compressor section and a fan root pressure rise of said fan section, said overall pressure ratio being equal to, or greater than, 36.
4 more elements
A gas turbine engine comprising:
- a fan section;
- a compressor section, including at least a first compressor section and a second compressor section;
- a turbine section including at least one turbine to drive said second compressor section and a fan drive turbine to drive at least a gear arrangement to drive said fan section;
- wherein a power ratio is provided by the combination of said first compressor section and said second compressor section, with said power ratio being provided by a second power input to said second compressor section divided by a first power input to said first compressor section, said power ratio being equal to or less than 1.4;
- and
- wherein an overall pressure ratio is provided by the combination of said first compressor section, said second compressor section and a fan root pressure rise of said fan section, said overall pressure ratio being equal to or greater than 36.
3 more elements
A method of designing a gas turbine engine comprising:
- providing a fan section;
- providing a compressor section, including a first compressor section and a second compressor section;
- providing a turbine section including at least one turbine to drive said second compressor section and a fan drive turbine to drive said fan section via a gear arrangement;
- wherein a power ratio is provided by the combination of said first compressor section and said second compressor section, with said power ratio being provided by a second power input to said second compressor section divided by a first power input to said first compressor section, said power ratio is equal to or less than 1.4 at a predetermined design target;
- and
- wherein an overall pressure ratio is provided by the combination of said first compressor section, said second compressor section and a fan root pressure rise of said fan section, said overall pressure ratio being equal to or greater than 36 at the predetermined design target.
3 more elements
Dependencies are inferred from the claim text.