Cooling system of a stator assembly for a gas turbine engine having a variable cooling flow mechanism and method of operation

Patent metadata

Field	Value
Publication number	US-10094229-B2
Application number	US-201514811122-A
Country	US
Kind code	B2
Filing date	Jul 28, 2015
Priority date	Jul 28, 2014
Publication date	Oct 9, 2018
Grant date	Oct 9, 2018

Abstract

A cooling system integrated into a stator assembly of a gas turbine engine has an on-board injector or cooling nozzle located for cooling of a rotor assembly. The nozzle may be generally annular and may contain a plurality of pivoting airfoils circumferentially spaced from one-another for directing cooling air flow from the nozzle and generally toward a plurality of holes in a cover of the rotor assembly. The pivoting airfoils are adapted to move between a spoiled state where the mass flow of cooling air is reduced, and to an optimal state where the mass flow is increased. The system may further include a plurality of fixed airfoils in the nozzle with adjacent fixed airfoils defining a discharge orifice in the nozzle. Each one of the plurality of pivoting airfoils may be located in a respective discharge orifice.

First claim

What is claimed is:

1. A variable cooling flow mechanism adapted to be secured to an annular cooling flow nozzle of a stator assembly of a gas turbine engine for controlling the mass flow of cooling air toward a downstream rotor assembly, the mechanism comprising:
a plurality of airfoils disposed in the nozzle and spaced circumferentially from one another about an engine axis, wherein at least some of the plurality of airfoils are constructed and arranged to move for controlling cooling air flow mass rate through the nozzle;
a sync ring centered to the engine axis and constructed and arranged to move the at least some of the plurality of airfoils simultaneously;
a drive linkage constructed and arranged to move the sync ring circumferentially, wherein the drive linkage extends radially from the sync ring and through a vane of the stator assembly.

2. The variable cooling flow mechanism set forth in claim 1 , wherein each one of the plurality of airfoils have a gear in operable contact with a set of teeth of the sync ring.

3. The variable cooling flow mechanism set forth in claim 1 , wherein the sync ring is disposed radially outward from the plurality of nozzles.

4. The variable cooling flow mechanism set forth in claim 1 , further comprising:
at least one actuator disposed radially outward of the vane and constructed and arranged to move the linkage.

5. The variable cooling flow mechanism set forth in claim 4 , wherein the actuator is constructed and arranged to rotate the linkage.

6. The variable cooling flow mechanism set forth in claim 5 , wherein the linkage includes a gear in operable contact with a set of teeth of the sync ring for moving the sync ring.

7. The variable cooling flow mechanism set forth in claim 1 , wherein the plurality of airfoils move between a first position and a second position.

8. A cooling system integrated into a stator assembly of a gas turbine engine for flowing cooling air toward a downstream rotor assembly, the cooling system comprising:
an annular nozzle concentric to an engine axis and for flowing cooling air generally toward the rotor assembly;
a plurality of fixed airfoils circumferentially spaced from one-another and disposed in the nozzle with adjacent fixed airfoils circumferentially defining a plurality of discharge orifices;
a plurality of pivoting airfoils with each pivoting airfoil disposed in a respective discharge, orifice of the plurality of discharge orifices, wherein each one of the plurality of pivoting airfoils has a leading edge portion projecting outward from a pivoting axis and a trailing edge portion projecting outward from the pivoting axis, and wherein each one of the plurality of pivoting airfoils pivots between a first position and a second position with at least one of the leading and trailing edge portions being closer to respective adjacent fixed airfoils when in the first position as opposed to the second position; and
a sync ring centered to the engine axis and constructed and arranged to move the plurality of pivoting airfoils simultaneously.

9. The cooling system set forth in claim 8 , further comprising:
a drive linkage extending radially outward from the sync ring and constructed and arranged to move the sync ring in a circumferential direction.

10. The cooling system set forth in claim 9 , further comprising:
an actuator disposed radially outward from the stator assembly and constructed and arranged to actuate the drive linkage.

11. The cooling system set forth in claim 10 , further comprising:
a controller for sending electronic signals to the actuator based on at least one of rotor speed, throttle position, and variable geometry condition.

12. The cooling system set forth in claim 8 , wherein the plurality of pivoting airfoils are arcuate in cross section.

13. A method of operating a cooling system of a gas turbine engine to provide cooling air to a turbine section of the gas turbine engine comprising the steps of:
moving one or more of a plurality of airfoils disposed in a cooling airflow nozzle into a first position when the gas turbine engine is operating at low rotor speed; and
moving the one or more of the plurality of airfoils into a second position when the gas turbine engine is operating at cruising speed;
wherein a sync ring centered to the engine axis is constructed and arranged to move the one or more of the plurality of airfoils simultaneously; and
wherein each of the one or more of the plurality of airfoils has a gear in operable contact with a set of teeth of the sync ring.

14. The method of operating the cooling system set forth in claim 13 , wherein the cooling air flow mass rate is reduced when in the first state.

Assignees

• United Technologies Corp

Inventors

• Snyder Brooks E
• Mccaffrey Michael G
• Slavens Thomas N

Classifications

• F01D5/081

  Cooling fluid being directed on the side of the rotor disc or at the roots of the blades (F01D5/087 takes precedence) · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F01D9/065

  Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids (see also F01D25/16, F01D25/24 and F01D25/26) · CPC title

• F01D17/162

  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

• F01D5/08

  Heating, heat-insulating or cooling means {(specially adapted for radial flow machines or engines F01D5/04)} · CPC title