Rotor for a turbo-machine and a related method

Patent metadata

Field	Value
Publication number	US-10145247-B2
Application number	US-201514602599-A
Country	US
Kind code	B2
Filing date	Jan 22, 2015
Priority date	Feb 21, 2014
Publication date	Dec 4, 2018
Grant date	Dec 4, 2018

Abstract

A rotor for a turbo-machine, the rotor having a rotational axis and circumferentially spaced-apart radially extending blades of aerofoil configuration, each blade having a suction side, an oppositely directed pressure side, and a pair of oppositely directed snubbers each of which extends from a respective side towards a circumferentially adjacent blade and presents an abutment surface for abutment with the abutment surface of a respective adjacent snubber extending from the adjacent blade. Each snubber is configured such that its abutment surface makes an acute snubber angle to the axis of rotation. At least one pair of adjacent snubbers are configured such that their abutment surfaces are at an equal first snubber angle, with all of the other snubbers being configured such that their abutment surfaces are at equal second snubber angles. The first snubber angle is larger than the second snubber angle.

First claim

The invention claimed is:

1. A rotor for a turbo-machine, the rotor having a rotational axis and comprising:
a plurality of circumferentially spaced-apart and radially extending blades of aerofoil configuration,
each blade having a suction side and an oppositely directed pressure side,
each blade having a pair of oppositely directed snubbers that each extends from a respective side of the blade towards a circumferentially adjacent blade, the snubbers each providing an abutment surface for abutment with the abutment surface of a respective adjacent snubber extending from the adjacent blade,
each snubber being configured such that the abutment surface of each snubber forms an acute snubber angle with the rotational axis, and
only one pair of adjacent snubbers being configured such that the abutment surfaces of the only one pair of adjacent snubbers are at an equal first snubber angle, and all of the remaining snubbers being configured such that the abutment surfaces of the remaining snubbers are at equal second snubber angles, the first snubber angle is between 1 and 10 degrees greater than the second snubber angle.

2. The rotor according to claim 1 , wherein the first snubber angle is 5 degrees greater than the second snubber angle.

3. The rotor according to claim 1 , wherein each abutment surface is planar.

4. The rotor according to claim 1 , wherein the turbo-machine is provided in the form of a propulsive fan for a ducted-fan gas turbine engine.

5. The rotor according to claim 1 , wherein the rotor is provided in the form of a compressor rotor for a gas turbine engine.

6. A gas turbine engine having a rotor according to claim 1 .

7. A method of modifying a turbo-machine rotor of a type having a rotational axis and a plurality of circumferentially spaced-apart radially extending blades of aerofoil configuration,
each blade having a suction side and an oppositely directed pressure side,
each blade having a pair of oppositely directed snubbers that each extends from a respective side of the blade towards a circumferentially adjacent blade, the snubbers each providing an abutment surface for abutment with the abutment surface of a respective adjacent snubber extending from the adjacent blade, and
each snubber, prior to modification, being configured such that the abutment surface of each snubber forms an equal acute snubber angle with the rotational axis,
the method comprising the steps of:
removing only one circumferentially adjacent pair of the blades from the rotor and replacing the pair of blades with respective replacement blades, a first replacement blade of the replacement blades having a first modified snubber extending from the suction side of the first replacement blade, and a second replacement blade of the replacement blades having a second modified snubber extending from the pressure side of the second replacement blade,
wherein the first and second replacement blades are installed in the rotor such that the first modified snubber and the second modified snubber provide respective abutment surfaces for abutment with one another, the abutment surface of the first modified snubber and the abutment surface of the second modified snubber both forming an equal modified acute snubber angle with the axis of rotation, the modified snubber angle being between 1 and 10 degrees greater than the snubber angle of all the remaining snubbers in the rotor.

8. The method according to claim 7 , wherein the method includes replacing only a single pair of blades in the rotor.

9. The method according to claim 7 , wherein the modified snubber angle is 5 degrees larger than the snubber angle of all the remaining snubbers in the rotor when the replacement blades are installed in the rotor.

10. The method according to claim 7 , wherein the method is performed on a rotor in the form of a propulsive fan for a ducted-fan gas turbine engine.

11. The method according to claim 7 , wherein the method is performed on a rotor in the form of a compressor rotor for a gas turbine engine.

Assignees

• Rolls Royce Plc

Inventors

• Orford Michael P

Classifications

• F04D29/668

  damping or preventing mechanical vibrations · CPC title

• F05D2260/96

  Preventing, counteracting or reducing vibration or noise · CPC title

• F01D5/225 Primary

  by shrouding · CPC title

• F04D29/324

  Blades · CPC title

• F05D2250/38

  angled, e.g. sweep angle · CPC title