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US 11,231,043 B2Granted
Gas turbine engine with ultra high pressure compressor
AssigneeGeneral Electric Company
InventorsVeeraraju Vanapalli, Bhaskar Nanda Mondal, Jagata Laxmi Narasimharao, Tsuguji Nakano, Subramanian Narayanan
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Abstract
The present disclosure is directed to a gas turbine engine including a compressor rotor. The compressor rotor includes a first stage compressor airfoil defined at an upstream-most stage of the compressor rotor. The first stage compressor airfoil defines a first stage pressure ratio of at least approximately 1.7 during operation of the gas turbine engine at a tip speed of at least approximately 472 meters per second.
Claims20
A gas turbine engine, comprising:
- a compressor rotor comprising a first stage compressor airfoil defined at an upstream-most stage of the compressor rotor,
- wherein the first stage compressor airfoil comprises a nickel-based material,
- wherein the first stage compressor airfoil defines a radius ratio of an inner radius of the first stage compressor airfoil within a core flowpath versus an outer radius of the first stage compressor airfoil within the core flowpath,
- wherein the radius ratio is greater than or equal to 0.2 and less than 0.4, and
- wherein the first stage compressor airfoil is structured to operate at a first stage pressure ratio of between 1.7 and 1.9 at a tip speed of between 472 and 564 meters per second.
2 more elements
A gas turbine engine, comprising:
- a core engine comprising:
- a compressor rotor comprising a first stage compressor airfoil defined at an upstream-most stage of the compressor rotor, wherein the first stage compressor airfoil is structured to operate at a first stage pressure ratio between 1.7 and 1.9 at a tip speed between 472 and 564 meters per second;
- a first turbine rotor coupled to the compressor rotor via a first shaft, wherein the first turbine rotor and the compressor rotor are together rotatable via the first shaft;
- and
- a combustor assembly disposed between the compressor rotor and the first turbine rotor in direct serial flow arrangement,
- wherein the first stage compressor airfoil comprises a nickel-based material,
- wherein the first stage compressor airfoil defines a radius ratio of an inner radius of the first stage compressor airfoil within a core flowpath versus an outer radius of the first stage compressor airfoil within the core flowpath,
- wherein the radius ratio is greater than or equal to 0.2 and less than 0.4.
5 more elements
Dependencies are inferred from the claim text.