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US 2019/0101001 A1Published application
Gas turbine engine airfoil
AssigneeUnited Technologies Corporation
InventorsTimothy Charles Nash, Wolfgang Balzer
Life of this patent
Estimating the term…
Abstract
A component for a gas turbine engine includes a platform that has a radially inner side and a radially outer side. A root portion extends from the radially inner side of the platform. An airfoil extends from a radially outer side of the platform. The airfoil includes a pressure side that extends between a leading edge and a trailing edge. A suction side extends between the leading edge and the trailing edge. A ratio of maximum thickness to axial chord length is between 0.40 (Tmax/bx) and 0.65 (Tmax/bx).
Claims20
A component for a gas turbine engine comprising:
- a platform having a radially inner side and a radially outer side;
- a root portion extending from the radially inner side of the platform;
- and
- an airfoil extending from a radially outer side of the platform, the airfoil including:
- a pressure side extending between a leading edge and a trailing edge;
- a suction side extending between the leading edge and the trailing edge;
- and
- a ratio of maximum thickness to axial chord length of between 0.40 (Tmax/bx) and 0.65 (Tmax/bx).
5 more elements
A gas turbine engine comprising:
- a compressor section and a turbine section;
- and
- a circumferential array of airfoils located in one of the compressor section and the turbine section, wherein each of the airfoils include:
- a pressure side extending between a leading edge and a trailing edge;
- a suction side extending between the leading edge and the trailing edge;
- and
- a ratio of maximum thickness to axial chord length of between 0.40 (Tmax/bx) and 0.65 (Tmax/bx).
4 more elements
Dependencies are inferred from the claim text.