Stator vane adjusting device of a gas turbine

Patent metadata

Field	Value
Publication number	US-9453426-B2
Application number	US-201314073157-A
Country	US
Kind code	B2
Filing date	Nov 6, 2013
Priority date	Nov 7, 2012
Publication date	Sep 27, 2016
Grant date	Sep 27, 2016

Abstract

A stator vane adjusting device of a gas turbine has a plurality of stator vanes each rotatable about a radial axis 44 and arranged in at least two radial planes, as well as at least one stator vane adjusting ring connected to the respective stator vanes and rotatable in the circumferential direction by at least one actuating device. The actuating device includes a crankshaft element rotatable about a stationary pivot axis by an actuator. A first lever is articulated by a joint to the stator vane adjusting ring, with its free end being connected by a joint to a center area of a second lever, the second lever being mounted at its one end on a stationary pivot point and at its other end being linked by a joint to a third lever, which is mounted by a joint at its free end on the crankshaft element.

First claim

The invention claimed is:

1. A stator vane adjusting device of a gas turbine having:
a plurality of stator vanes each rotatable about a radial axis and arranged in at least two radial planes,
at least one stator vane adjusting ring connected to the respective stator vanes and rotatable in a circumferential direction by at least one actuating device, with the at least one actuating device including a crankshaft element rotatable about a stationary pivot axis by an actuator,
a first lever, a second lever and a third lever, the first lever being articulated by a joint to the at least one stator vane adjusting ring, a free end of the first lever being connected by a joint to a center area of the second lever, with the second lever being mounted at one end thereof on a stationary pivot point and at another end thereof being linked by a joint to the third lever, which is mounted by a joint at a free end thereof on the crankshaft element.

2. The device in accordance with claim 1 , wherein the stationary pivot point of the second lever is arranged radially inside the crankshaft element relative to an engine axis of the gas turbine.

3. The device in accordance with claim 1 , wherein the stationary pivot point of the second lever is arranged radially outside the crankshaft element relative to an engine axis of the gas turbine.

4. The device in accordance with claim 1 , wherein the crankshaft element includes at least a first and a second cam element, with the third lever being articulated to the first cam element and the actuator being coupled to the second cam element.

5. The device in accordance with claim 1 , and further comprising an intermediate lever, with the actuator being connected to the crankshaft element via the intermediate lever.

6. The device in accordance with claim 1 , wherein the at least one stator vane adjusting ring includes a plurality of stator vane adjusting rings which are each coupled to the crankshaft element by a first, second and third lever.

7. The device in accordance with claim 1 , wherein the device converts a linear movement of the actuator into a non-linear rotation of the at least one stator vane adjusting ring.

8. The device in accordance with claim 1 , wherein the lengths of the first second and third lever are selected to provide a transmission with a distinctly non-constant transmission ratio.

Assignees

• Rolls Royce Deutschland Ltd & Co Kg

Inventors

• Klauke Thomas
• Mojem Mats
• Rajaratnam Nishanth

Classifications

• F02C9/20

  by throttling; by adjusting vanes · CPC title

• F01D17/162 Primary

  for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line (F01D17/167 takes precedence) · CPC title

• F05D2260/50

  Kinematic linkage, i.e. transmission of position · CPC title

• F01D9/045 Primary

  for radial flow machines or engines · CPC title

• F04D29/563

  specially adapted for elastic fluid pumps · CPC title