Patent · US Active

Rotor blade for a gas turbine engine

US10808539B2 · kind B2 · utility

1Cited by

8References

14Claims

0Family size

Assignee

RAYTHEON TECHNOLOGIES CORPORATION · US

Inventors

Taryn Narrow · Glastonbury, US
Matthew E. Bintz · Town of West Hartford, US
Lucas D. Sorensen · Middletown, US
Daniel J. Monahan · Cromwell, US
Steven D. Roberts · Moodus, US
Jordan T. Wall · Hartford, US
Yuan Dong · Glastonbury, US
Lisa I. Brilliant · Middletown, US
Andrew J. Murphy · New Garden Township, US

Key dates

Filing date	Jul 25, 2016
Grant date	Oct 20, 2020
Priority date	—
Expiry date	Jan 30, 2038

Classification

Technology area (CPC F)Mechanical Engineering; Lighting; Heating
CPC primaryF05D2250/314
WIPO fieldEngines, pumps, turbines
WIPO sectorMechanical engineering

Abstract

A rotor blade for a gas turbine engine includes a blade extending from a root and a contoured tip portion at a first end of the blade. The first end is opposite the root. The contoured tip portion includes a first sloped region and a second sloped region. The second sloped region is steeper than the first sloped region, relative to a platform.

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