Hollow turbine blade stiffening
AssigneePratt & Whitney Canada Corp.
InventorsSteven John Fett, Scott Walker Smith, Bich Nhu Le
Life of this patent
Estimating the term…
Abstract
An apparatus and method for at least one of stiffening a rotor blade of a gas turbine engine and raising a natural vibration frequency of the blade. The blade has a recess extending radially and inwardly into the blade. A reinforcing element is provided in the recess at a selected position to thereby allow a large blade chord at the tip end of the blade.
Claims11
A rotor blade of a gas turbine engine, the rotor blade comprising:
- an airfoil extending from a root end to a tip end, the root end mounted to a connection apparatus for securing the blade to the engine, the airfoil having a leading edge, a trailing edge and an outer periphery, the outer periphery defined by a pressure side and a suction side each extending from the leading edge to the trailing edge;
- an open recess defined in the tip end of the airfoil extending from the tip end towards the root end, the recess having first and second sides corresponding to the airfoil pressure and suction sides;
- and
- at least one reinforcing element disposed in the recess and extending from the first side to the second side, the element disposed in the recess in a position adapted, in use, to minimize a trailing edge bending of the blade by reason of said position of the element in the recess.
A rotor blade of a gas turbine engine, the rotor blade comprising:
- an airfoil extending from a root end to a tip end, the root end mounted to a connection apparatus for securing the blade to the engine, the airfoil having a leading edge, a trailing edge and an outer periphery, the outer periphery defined by a pressure side and a suction side each extending from the leading edge to the trailing edge;
- an open recess defined in the tip end of the airfoil extending from the tip end towards the root end, the recess having first and second sides corresponding to the airfoil pressure and suction sides, the recess having a widest point, the widest point being that having a widest perpendicular distance between the first side and the second side;
- and
- at least one reinforcing element disposed in the recess and extending from the first side to the second side, the element positioned in the recess aft of said widest point.
A method for impeding second mode bending in a trailing edge portion of a hollow rotor blade of a gas turbine engine, the hollow blade having a recess defined in a tip end thereof, the recess extending into the blade toward a root end, the method comprising the steps of:
- providing a desired blade geometry;
- analyzing the geometry to determine at least one second mode bending characteristic of the blade geometry;
- and
- providing a reinforcing element the recess of the blade at a selected position of the blade, the selected position adapted to permit the element to minimize second mode bending in the trailing edge portion of the blade.
Dependencies are inferred from the claim text.