Patent · US Active

Gas turbine engine airfoil

US10563512B2 · kind B2 · utility

0Cited by

6References

18Claims

0Family size

Assignee

UNITED TECHNOLOGIES CORPORATION · US

Inventors

Timothy Charles Nash · Town of East Hartford, US
Carey Clum · Town of East Hartford, US

Key dates

Filing date	Oct 25, 2017
Grant date	Feb 18, 2020
Priority date	—
Expiry date	Dec 22, 2037

Classification

Technology area (CPC Y)Emerging Cross-Sectional Technologies
CPC primaryY02T50/60
WIPO fieldEngines, pumps, turbines
WIPO sectorMechanical engineering

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 the 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 leading edge radius to maximum thickness is between 0.40 (r/Tmax) and 0.45 (r/Tmax) and a ratio of leading edge radius to axial chord length is between 0.17 (r/bx) and 0.27 (r/bx).

Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.