Stator vane assembly

Patent metadata

Field	Value
Publication number	US-10233769-B2
Application number	US-201514746052-A
Country	US
Kind code	B2
Filing date	Jun 22, 2015
Priority date	Jul 18, 2014
Publication date	Mar 19, 2019
Grant date	Mar 19, 2019

Abstract

Stator vane assembly includes plurality of vanes arranged in circumferential array, radially proximal mounting portion, radially distal mounting portion, and first latching mechanism. Each of plurality of vanes extends radially between radially proximal mounting portion and radially distal mounting portion, with each of plurality of vanes being pivotally mounted between radially proximal mounting portion and radially distal mounting portion. Plurality of vanes is movable between first arrangement allowing gas to flow across vanes, and second arrangement blocking gas flow across vanes. Pivot axis of each of plurality of vanes is offset from the line of aerodynamic center of pressure of vane towards trailing edge of vane, and first latching mechanism holds plurality of vanes in first arrangement. Upon receipt of signal, first latching mechanism releases plurality of vanes so that gas flow through vane assembly causes plurality of vanes to move from first arrangement to second arrangement.

First claim

What is claimed is:

1. A stator vane assembly comprising:
a plurality of vanes arranged in a circumferential array;
a radially proximal mounting portion;
a radially distal mounting portion; and
a controllable first latch;
each of the plurality of vanes extending radially between the radially proximal mounting portion and the radially distal mounting portion;
each of the plurality of vanes being pivotally mounted between the radially proximal mounting portion and the radially distal mounting portion;
the plurality of vanes being movable between a first arrangement allowing gas to flow across the plurality of vanes, and a second arrangement blocking gas flow across the plurality of vanes;
wherein a pivot axis of each of the plurality of vanes is offset from a line of aerodynamic centre of pressure of each of the plurality of vanes towards a trailing edge of each of the plurality of vanes; and
the controllable first latch holds the plurality of vanes in the first arrangement and, upon receipt of a control signal, releases the plurality of vanes so that the gas flow through the stator vane assembly causes the plurality of vanes to move from the first arrangement to the second arrangement.

2. The stator vane assembly as claimed in claim 1 , further comprising a limit stop, the limit stop defining an angular position of each of the plurality of vanes when the plurality of vanes are positioned in the second arrangement.

3. The stator vane assembly as claimed in claim 1 , further comprising a damper that controls a rate of angular rotation of each of the plurality of vanes during the vane's transition from the first arrangement to the second arrangement.

4. The stator vane assembly as claimed in claim 1 , further comprising a second latch, and wherein after the plurality of vanes have moved to the second arrangement, the second latch retains the plurality of vanes in the second arrangement.

5. The stator vane assembly as claimed in claim 1 , further comprising an actuator, and wherein after the plurality of vanes have moved to the second arrangement, the actuator moves the plurality of vanes from the second arrangement to the first arrangement.

6. The stator vane assembly as claimed in claim 1 , wherein the first latch comprises a plurality of actuatable locking pins, each of the plurality of actuatable locking pins corresponding to a respective one of the plurality of vanes.

7. The stator vane assembly as claimed in claim 1 , wherein the first latch comprises an electromagnet configured to hold the plurality of vanes in the first arrangement when the electromagnet is energised.

8. The stator vane assembly as claimed in claim 1 , further comprising a unison ring, each of the plurality of vanes being engageably coupled to the unison ring, wherein the first latch comprises an electromagnet configured to position the unison ring such that the plurality of vanes are in the first arrangement when the electromagnet is energised.

9. The stator vane assembly as claimed in claim 1 , wherein the aerodynamic centre of pressure of each of the plurality of vanes is between a leading edge of each of the plurality of vanes and the trailing edge of each of the plurality of vanes in a leading edge-to-trailing edge cross-section of each of the plurality of vanes, and the pivot axis of each of the plurality of vanes is offset from the aerodynamic centre of pressure of each of the plurality of vanes towards the trailing edge.

10. A method of controlling an airflow through a stator vane assembly, the stator vane assembly comprising a plurality of circumferentially arranged vanes, the method comprising the steps of:
(i) arranging a gas flow through the stator vane assembly;
(ii) positioning the plurality of vanes in a first arrangement and secured therein by a first latch, allowing a gas flow through the stator vane assembly; and
(iii) controllably releasing the first latch to enable the gas flow impinging on the vanes to move the plurality of vanes from the first arrangement to a second arrangement in which gas flow through the stator vane assembly is blocked.

Assignees

• Rolls Royce Plc

Inventors

• Scothern David Peter

Classifications

• F01D17/12 Primary

  arranged in stator parts · CPC title

• F01D9/02 Primary

  Nozzles; Nozzle boxes; Stator blades; Guide conduits {, e.g. individual nozzles (nozzle boxes F01D9/047)} · CPC title

• F01D21/02

  Shutting-down responsive to overspeed · CPC title

• F01D17/16

  by means of nozzle vanes · CPC title

• F01D9/041

  using blades (F01D5/148 takes precedence) · CPC title