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US 9,429,026 B2Granted
Decoupled compressor blade of a gas turbine
AssigneeRolls-Royce Deutschland Ltd & Co KG
InventorKarl Schreiber
Life of this patent
Estimating the term…
Abstract
The present invention relates to a compressor blade of a gas turbine having an airfoil made of a fiber-reinforced plastic, which is fastened by means of a blade root to a disk, as well as a metallic leading-edge element, which is arranged on the leading-edge side of the airfoil and partially encompasses the latter, with the leading-edge element itself being fastened to the disk.
Claims19
A compressor blade system of a gas turbine comprising:
- a rotor disk;
- a compressor blade, comprising:
- an airfoil made of a fiber-reinforced plastic and including a pressure side surface, a suction side surface, a leading edge and a blade root, the airfoil attached to the rotor disk by the blade root,
- a metallic leading edge element arranged on the leading edge and partially encompassing the leading edge,
- the leading edge element being attached to the rotor disk separately from the airfoil and at least partially decoupled from the airfoil to allow relative motion in a radial direction with respect to the rotor disk between the leading edge element and the airfoil.
2 more elements
A compressor blade system of a gas turbine comprising:
- a rotor disk;
- a compressor blade, comprising:
- an airfoil made of a fiber-reinforced plastic and including a pressure side surface, a suction side surface, a leading edge and a blade root, the airfoil attached to the rotor disk by the blade root,
- a metallic leading edge element arranged on the leading edge and partially encompassing the leading edge,
- the leading edge element being attached to the rotor disk separately from the airfoil;
- the leading edge element including a radially extending first partial element and a radially extending second partial element connected to one another;
- an inflow edge element arranged in an area of an inflow side of the compressor blade between the first partial element and the second partial element.
4 more elements
A compressor blade system of a gas turbine comprising:
- a rotor disk;
- a compressor blade, comprising:
- an airfoil made of a fiber-reinforced plastic and including a pressure side surface, a suction side surface, a leading edge and a blade root, the airfoil attached to the rotor disk by the blade root,
- a metallic leading edge element arranged on the leading edge and partially encompassing the leading edge,
- the leading edge element being attached to the rotor disk separately from the airfoil for independent introduction of forces, decoupled from one another, into the disk.
2 more elements
Dependencies are inferred from the claim text.