Patent · US Active

Blade for a gas turbomachine

US9896940B2 · kind B2 · utility

1Cited by

0References

15Claims

0Family size

Assignee

MTU Aero Engines AG · DE

Inventors

Alexander Boeck · Munich, DE
Norbert Huebner · Dachau, DE
Sven Schmid · Munich, DE

Key dates

Filing date	Jul 8, 2014
Grant date	Feb 20, 2018
Priority date	—
Expiry date	Dec 22, 2035

Classification

Technology area (CPC F)Mechanical Engineering; Lighting; Heating
CPC primaryF05D2240/304
WIPO fieldEngines, pumps, turbines
WIPO sectorMechanical engineering

Abstract

A blade, in particular a rotor blade or a stator vane, for a gas turbomachine, in particular a turbojet engine, the blade having an airfoil (1) for deflecting a flow of working fluid and a first platform (3) connected thereto, in particular integrally connected thereto, to radially bound a flow duct for the working fluid, the airfoil having a suction side and a pressure side (1.1) which are connected at a leading edge (1.2) and at a trailing edge (1.3). The trailing edge has a first minimum wall thickness in a first region (A) of a radial longitudinal extent (R) of the airfoil proximal to the first platform (3), and a maximum wall thickness that is smaller than the first minimum wall thickness in a platform-distal region (C) of the radial longitudinal extent.

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