Operability geared turbofan engine including compressor section variable guide vanes
AssigneeRtx Corporation
InventorsGlenn Levasseur, Gabriel L. Suciu, Gary M. Stetson
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Abstract
A gas turbine engine includes a propulsor having a plurality of blades, a compressor section including a first compressor and a second compressor aft of the first compressor. The first compressor includes at least one array of first variable guide vanes that control operation of the first compressor. The second compressor includes at least one array of second variable guide vanes that control operation of the second compressor. A turbine section includes a first turbine and a second turbine. A geared architecture is driven by the second turbine for rotating the propulsor.
Claims30
A gas turbine engine comprising:
- a propulsor including a plurality of blades rotatable about an engine axis;
- a compressor section including a first compressor and a second compressor aft of the first compressor relative to the engine axis, wherein the first compressor includes at least one array of first variable guide vanes that control operation of the first compressor, the second compressor includes at least one array of second variable guide vanes that control operation of the second compressor, a pressure ratio of the first compressor is in the range of 4:1 to 7:1, and a pressure ratio of the second compressor is in the range 8:1 to 15:1;
- a turbine section including a first turbine and a second turbine arranged aft of the first turbine relative to the engine axis;
- a geared architecture driven by the second turbine for rotating the propulsor about the axis;
- and
- wherein the propulsor has a total number of the blades, the total number of the blades being less than 20, and a ratio between the total number of the blades and a total number of turbine rotors of the second turbine is between 3.3 and 8.6.
Dependencies are inferred from the claim text.