Turbine stator vane with insert and flexible seal

Patent metadata

Field	Value
Publication number	US-9611755-B2
Application number	US-201414534489-A
Country	US
Kind code	B2
Filing date	Nov 6, 2014
Priority date	Nov 20, 2013
Publication date	Apr 4, 2017
Grant date	Apr 4, 2017

Abstract

An air cooled turbine stator vane with an impingement cooling insert secured within a hollow cavity, where seal slots are formed between the cavity and the insert in which a flexible seal is located, and where the cavity and the insert includes chordwise movement bumpers and sideways movement bumpers each having a gap to allow for relative movement of the insert within the cavity from thermals while maintaining a seal between the cavity and the insert. The flexible seal is an X-shaped seal having four contact surfaces with the seal slots so that a high relative movement can occur while still maintaining a tight seal. The insert includes a number of cross-over tubes connecting return air holes on the pressure side to impingement holes on the suction side of the insert.

First claim

I claim the following:

1. An air cooled turbine stator vane comprising:
an airfoil with a leading edge region and a trailing edge region and a pressure side wall and a suction side wall;
the airfoil being a hollow airfoil forming a cavity;
a first seal slot formed on an inside section of the hollow airfoil;
an impingement cooling insert located within the cavity;
a second seal slot formed on the impingement cooling insert and facing the first seal slot;
a plurality of chordwise movement bumpers formed on the inside section of the airfoil and on the impingement cooling insert to limit a chordwise movement of the impingement cooling insert relative to the cavity;
a plurality of sideways movement bumpers formed on the inner wall of the airfoil and on the impingement cooling insert to limit a sideways movement of the impingement cooling insert relative to the cavity;
a flexible seal secured within the first and second seal slots of the cavity and the impingement cooling insert; and,
a chordwise gap formed between the chordwise movement bumpers and a sideways gap formed between the sideways movement bumpers such that the flexible seal can a seal between the inside section of the hollow airfoil and the impingement cooling insert due to relative movement from thermal gradients.

2. The air cooled turbine stator vane of claim 1 , and further comprising:
the hollow airfoil includes a rib separating a forward cavity from an aft cavity;
each cavity includes a forward seal slot and an aft seal slot formed between an impingement cooling insert;
each forward seal slot and aft seal slot includes a chordwise movement bumper and a sideways movement bumper;
a flexible seal secured within each of the forward seal slots and the aft seals slots; and,
a gap formed between the chordwise movement bumper and a sideways movement bumper so that the flexible seals maintain a seal between the cavity and the insert due to relative movement from thermal gradients.

3. The air cooled turbine stator vane of claim 2 , and further comprising:
the rib includes an aft seal slot for the forward cavity and a forward seal slot for the aft cavity.

4. The air cooled turbine stator vane of claim 1 , and further comprising:
the flexible seal is an X-shaped seal with four points that each makes contact with a surface of the seal slots.

5. An air cooled turbine stator vane comprising:
an airfoil with a hollow cavity;
an impingement cooling insert secured within the hollow cavity of the airfoil;
the impingement cooling insert having a pressure side surface and a suction side surface enclosing a cooling air supply cavity;
the pressure side surface having an arrangement of pressure side impingement cooling holes connected to the cooling air supply cavity;
the pressure side surface having an arrangement of return air holes;
the suction side surface having an arrangement of suction side impingement cooling holes; and,
the impingement cooling insert having a plurality of cross-over tubes that extend from a top to bottom and side to side regions of the suction side surface of the impingement cooling insert and connect the return air holes on the pressure side surface to the impingement cooling air holes on the suction side surface.

6. The air cooled turbine stator vane of claim 5 , and further comprising:
the impingement cooling insert includes a forward seal slot and an aft seal slot; and,
a flexible seal secured within each of the forward seal slot and the aft seal slot to produce a seal between cooling air on the pressure side and the suction side of the insert.

7. The air cooled turbine stator vane of claim 5 , and further comprising:
each of the forward seal slot and the aft seal slot includes a chordwise movement bumper surface and a sideways movement bumper surface to limit a relative movement of the insert with respect to the hollow cavity of the airfoil such that the flexible seal maintains a seal.

8. The air cooled turbine stator vane of claim 6 , and further comprising:
the flexible seal is an X-shaped seal having four contacts surfaces within a seal slot.

9. An air cooled turbine stator vane comprising:
an airfoil with a leading edge region and a trailing edge region and a pressure side wall and a suction side wall;
the airfoil being a hollow airfoil forming a cavity;
a first seal slot formed on an inside section of the hollow airfoil;
an impingement cooling insert located within the cavity;
a second seal slot formed on the impingement cooling insert and aligned with the first seal slot;
a plurality of bumpers formed on an inside surface of the airfoil and on the impingement cooling insert to limit a movement of the impingement cooling insert relative to the airfoil;
a flexible seal secured within the first and second seal slots of the airfoil and the impingement cooling insert; and,
a gap formed between the plurality of bumpers of the airfoil and the impingement cooling insert such that the flexible seal can maintain a seal between the airfoil and the impingement cooling insert due to relative movement from thermal gradients.

10. The air cooled turbine stator vane of claim 9 , and further comprising:
the flexible seal is an X-shaped seal with four points that each makes contact with a surface of the first and second seal slots.

11. The air cooled turbine stator vane of claim 9 , and further comprising:
the impingement cooling insert having a pressure side surface and a suction side surface enclosing a cooling air supply cavity;
the pressure side surface having an arrangement of pressure side impingement cooling holes connected to the cooling air supply cavity;
the pressure side surface having an arrangement of return air holes;
the suction side surface having an arrangement of suction side impingement cooling holes; and,
the impingement cooling insert having a plurality of cross-over tubes that connect the return air holes on the pressure side surface to the impingement cooling air holes on the suction side surface.

Assignees

• Memmen Robert L
• Florida Turbine Tech Inc

Inventors

• Memmen Robert L

Classifications

• F05D2260/30

  Retaining components in desired mutual position · CPC title

• F01D25/12 Primary

  Cooling · CPC title

• F05D2250/75

  given by its similarity to a letter, e.g. T-shaped · CPC title

• F05D2260/201

  by impingement of a fluid · CPC title

• F01D11/003

  by packing rings; Mechanical seals · CPC title