Radial compressor blade clearance control system

• US 9,121,302 B2
• Filed: 07/12/2012
• Issued: 09/01/2015
• Est. Priority Date: 07/12/2012
• Status: Active Grant

• Current Assignee: Hamilton Sundstrand Corporation (Rtx Corporation)
• Original Assignee: Hamilton Sundstrand Corporation (Rtx Corporation)
• Inventors: Duong, Loc Quang, Hu, Xiaolan
• Primary Examiner(s): EDGAR, RICHARD A
• Application Number:
  US13/547,155
• Publication Number:
  US 20140017060A1
• Time in Patent Office: 1,146 Days
• Field of Search: 415/173.3, 415/174.2, 415/172.1, 415/173.2, 415/174.1
• US Class Current: 1/1
• CPC Class Codes: F01D 11/22 by mechanically actuating the stator or rotor components, e.g. moving shroud sections relative to the rotor
• CPC Class Codes: F01D 9/045 for radial flow machines or engines

Abstract

A diaphragm assembly includes a cylinder, a circular flange, and a diaphragm. The cylinder defines an axis and includes a first end and a second end opposite the first end. The circular flange is coaxial with the cylinder and at a greater radial distance from the axis than the cylinder. The diaphragm extends from the second end of the cylinder to the flange.

Claims

1. A diaphragm assembly comprises:

a cylinder defining an axis, the cylinder including

a first end; and

a second end opposite the first end;

a circular flange coaxial with the cylinder and at a greater radial distance from the axis than the cylinder;

a diaphragm extending from the second end of the cylinder to the flange; and

a first actuator connected to the second end of the cylinder to move the cylinder in an axial direction against a restoring force of the diaphragm.

2. The diaphragm assembly of claim 1, further comprising:

an inner fillet where the diaphragm extends from the second end of the cylinder, the inner fillet on a side of the diaphragm facing the first end of the cylinder; and

an outer fillet where the diaphragm extends to the flange, the outer fillet on a side of the diaphragm facing away from the first end of the cylinder.

3. The diaphragm assembly of claim 2, further comprising an inner radius at a maximum radial extent of the inner fillet and an outer radius at a minimum radial extent of the outer fillet;

a ratio of the outer radius to the inner radius is no less than 1.4 and no greater than 1.8.

4. The diaphragm assembly of claim 2, wherein the diaphragm tapers in thickness from an inner radius thickness at a maximum radial extent of the inner fillet to an outer radius thickness at a minimum radial extent of the outer fillet;

the inner radius thickness being greater than the outer radius thickness.

5. The diaphragm assembly of claim 4, wherein a ratio of the inner radius thickness to the outer radius thickness is no less than 2 and no greater than 4.

6. The diaphragm assembly of claim 4, wherein a ratio of a radius of curvature of the inner fillet to the inner radius thickness is no less than 3 and no greater than 6;

and a ratio of curvature of the outer fillet to the outer radius thickness is no less than 4 and no greater than 8.

7. The diaphragm assembly of claim 4, wherein the side of the diaphragm facing away from the first end of the cylinder forms a taper angle from a plane perpendicular to the axis of no less than 0 degrees and no greater than 15 degrees.

8. The diaphragm assembly of claim 7, wherein the side of the diaphragm facing the first end of the cylinder forms a taper angle from a plane perpendicular to the axis of no less than 0 degrees and no greater than 15 degrees.

9. A radial compressor comprising:

an impeller rotatable about an axis, the impeller including a frustoconical hub and a plurality of impeller blades extending radially from the hub;

a frustoconical shroud coaxial with the impeller and spaced a distance from the impeller blades to form a fluid flow path between the hub and the shroud;

a diaphragm assembly including;

a cylinder coaxial with and radially outward from a portion of the shroud, the cylinder having a first end connected to the shroud and a second end opposite the first end;

a circular flange coaxial with the cylinder and at a greater radial distance from the axis than the cylinder; and

a diaphragm extending from the second end of the cylinder to the flange; and

a first actuator connected to the second end of the cylinder to move the cylinder and shroud in an axial direction against a restoring force of the diaphragm and change the distance between the shroud and the impeller blades.

10. The radial compressor of claim 9, wherein the diaphragm assembly further includes:

an inner fillet where the diaphragm extends from the second end of the cylinder, the inner fillet on a side of the diaphragm facing the first end of the cylinder; and

an outer fillet where the diaphragm extends to the outer flange, the outer fillet on a side of the diaphragm facing away from the first end of the cylinder.

11. The radial compressor of claim 10, wherein the diaphragm tapers in thickness from an inner radius thickness at a maximum radial extent of the inner fillet to an outer radius thickness at a minimum radial extent of the outer fillet;

the inner radius thickness being greater than the outer radius thickness.

12. The radial compressor of claim 11, wherein a ratio of the inner radius thickness to the outer radius thickness is no less than 2 and no greater than 4.

13. The radial compressor of claim 11, wherein a ratio of a radius of curvature of the inner fillet to the inner radius thickness is no less than 3 and no greater than 6;

and a ratio of curvature of the outer fillet to the outer radius thickness is no less than 4 and no greater than 8.

14. The radial compressor of claim 11, wherein the side of the diaphragm facing away from the first end of the cylinder forms a taper angle from a plane perpendicular to the axis of no less than 0 degrees and no greater than 15 degrees.

15. The radial compressor of claim 14, wherein the side of the diaphragm facing the first end of the cylinder forms a taper angle from a plane perpendicular to the axis of no less than 0 degrees and no greater than 15 degrees.

16. The radial compressor of claim 10, further comprising a second actuator connected to the second end of the cylinder to move the cylinder and shroud in an axial direction against a restoring force of the diaphragm, the second actuator disposed about 180 degrees around the circumference of the cylinder from the first actuator.

17. The radial compressor of claim 10, further comprising a plurality of actuators connected to the second end of the cylinder to move the cylinder and shroud in an axial direction against a restoring force of the diaphragm, the first actuator and the plurality of actuators disposed substantially evenly around the circumference of the cylinder.

18. The radial compressor of claim 10, wherein the shroud includes a spring hook extending in a radial direction from a radially outward extending edge of the shroud.

19. A method for dynamically controlling a distance between impeller blades and a surrounding compressor shroud in a radial compressor of a gas turbine engine;

the method comprising;

measuring a compressor impeller inlet fluid temperature;

measuring a compressor impeller exit fluid pressure;

measuring a compressor impeller rotation rate;

determining a desired distance between the impeller blades and the shroud based on conditions represented by the measured compressor impeller inlet fluid temperature, the measured compressor impeller exit fluid pressure, and the measured compressor impeller rotation rate; and

commanding an actuator to move a diaphragm assembly attached to the shroud to an axial position corresponding to the desired distance.

20. The method of claim 19, further comprising providing feedback control by repeating the method of claim 19.