Gas turbine engine

Patent metadata

Field	Value
Publication number	US-10415412-B2
Application number	US-201715699314-A
Country	US
Kind code	B2
Filing date	Sep 8, 2017
Priority date	Sep 30, 2016
Publication date	Sep 17, 2019
Grant date	Sep 17, 2019

Abstract

A rotatable arrangement for a gas turbine engine comprises a plurality of blades having an aerofoil profile with a suction side, a pressure side, a leading edge and a trailing edge. A plurality of annulus fillers are provided between adjacent blades. A pressure side seal extends between a blade and an annulus filler on the pressure side of the blade, and a suction side seal extends between the blade and an annulus filler on the suction side of the blade. The suction side seal comprises a blocking member provided at an end of the suction side seal proximal to the trailing edge of the blade, the blocking member being configured to restrict recirculation of flow along the suction side of the blade.

First claim

We claim:

1. A rotatable arrangement for a gas turbine engine, the arrangement comprising:
a plurality of blades having an aerofoil profile with a suction side, a pressure side, a leading edge and a trailing edge,

a plurality of annulus fillers provided between adjacent blades;
a pressure side seal extending between a blade and an annulus filler on the pressure side of the blade; and
a suction side seal extending between the blade and an annulus filler on the suction side of the blade, the suction side seal having an axial extent greater than an axial extent of the pressure side seal;
wherein the suction side seal comprises a blocking member provided at an end of the suction side seal proximal to the trailing edge of the blade, the blocking member being configured to restrict recirculation of flow along the suction side of the blade.

2. The arrangement according to claim 1 , wherein the blocking member is configured to move between a first position and a second position, in the first position a gap is provided at a trailing edge of the blade and in the second position the gap is sealed.

3. The arrangement according to claim 2 , wherein the blocking member is arranged to rotate to move between the first position and the second position.

4. The arrangement according to claim 2 , wherein the gap at the trailing edge of the blade is between adjacent annulus fillers.

5. The arrangement according to claim 4 , wherein at least a portion of the blocking member is arranged to rotate and move axially to move from the first position to the second position.

6. The arrangement according to claim 4 , wherein the suction side seal comprises an activation section and a flap, wherein the activation section moves the flap between the first position and the second position.

7. The arrangement according to claim 6 , wherein the activation section includes a pleated portion, and the pleated portion is arranged such that in the first position there is a gap between the pleated portion and the suction side of the blade and in the second position the pleated portion straightens such that the previously pleated portion is aligned with and adjacent to the suction side of the blade.

8. The arrangement according to claim 6 , wherein in the second position the flap extends across a gap between two adjacent annulus fillers.

9. The arrangement according to claim 2 , wherein the gap is between a trailing edge of the blade and the suction side seal.

10. The arrangement according to claim 9 , wherein the blocking member is provided transverse to a principal direction of the suction side seal.

11. The arrangement according to claim 10 , wherein the blocking member is provided at between 70 and 90° to the suction side seal at the trailing edge.

12. The arrangement according to claim 1 , wherein the blocking member comprises a sharp transition between the exit of a flow path over the blocking member and adjacent surfaces.

13. The arrangement according to claim 1 , wherein at least a portion of the blocking member is made from rubber or an elastomeric material.

14. The arrangement according to claim 1 , wherein the blocking member is made from the same material as the suction side seal.

15. The arrangement according to claim 1 , wherein the suction side seal and/or the blocking member comprise one or more stiffening members.

16. The arrangement according to claim 1 , wherein the suction side seal is generally T shaped with the widest part of the seal being positioned proximal to a gas washed surface of the annulus filler.

17. The arrangement according to claim 1 , wherein the arrangement is a fan, and the blades are fan blades.

18. A gas turbine engine comprising a rotatable arrangement for a gas turbine engine, the arrangement comprising:
a plurality of blades having an aerofoil profile with a suction side, a pressure side, a leading edge and a trailing edge,
a plurality of annulus fillers provided between adjacent blades;
a pressure side seal extending between a blade and an annulus filler on the pressure side of the blade; and
a suction side seal extending between the blade and an annulus filler on the suction side of the blade;
wherein the suction side seal comprises a blocking member provided at an end of the suction side seal proximal to the trailing edge of the blade, the blocking member being configured to restrict recirculation of flow along the suction side of the blade, wherein the blocking member is configured to move between a first position and a second position, in the first position a gap is provided at a trailing edge of the blade and in the second position the gap is sealed.

19. A rotatable arrangement for a gas turbine engine, the arrangement comprising:
a plurality of blades having an aerofoil profile with a suction side, a pressure side, a leading edge and a trailing edge,

a plurality of annulus fillers provided between adjacent blades;
a pressure side seal extending between a blade and an annulus filler on the pressure side of the blade; and
a suction side seal extending between the blade and an annulus filler on the suction side of the blade;
wherein the suction side seal comprises a blocking member provided at an end of the suction side seal proximal to the trailing edge of the blade, the blocking member being configured to restrict recirculation of flow along the suction side of the blade, wherein a gas washed surface of the blocking member is contoured such that air flow exiting a flow path over the blocking member exits in an axial direction.

Assignees

• Rolls Royce Plc

Inventors

• Hicklin Mark J
• Shipley Neil A
• Swan Daniel J

Classifications

• F01D11/008 Primary

  by spacer elements between the blades, e.g. independent interblade platforms · CPC title

• F01D11/006 Primary

  Sealing the gap between rotor blades or blades and rotor · CPC title

• F05D2240/306

  related to the suction side of a rotor blade · CPC title

• F05D2240/305

  related to the pressure side of a rotor blade · CPC title

• F05D2240/304

  related to the trailing edge of a rotor blade · CPC title