Inflow radial turbine with reduced bore stress concentration

Patent metadata

Field	Value
Publication number	US-2016208688-A1
Application number	US-201514600390-A
Country	US
Kind code	A1
Filing date	Jan 20, 2015
Priority date	Jan 20, 2015
Publication date	Jul 21, 2016
Grant date	—

Abstract

A gas turbine engine is provided comprising an impeller configured to rotate about an axis. A combustor is in fluid communication with the impeller. An inflow radial turbine is aft of the impeller and in fluid communication with the combustor. The inflow radial turbine includes a rotor with a bore having a flat bore end configured to rotate about the axis. A radial turbine is also provided comprising a rotor configured to rotate about an axis and a bore defined by a proximal portion of the rotor. The bore may have a flat bore end. A rotor is further provided comprising a disk configured to rotate about an axis and a bore partially through the disk along the axis. The bore may comprise a flat section extending radially from the axis and a curved section aft of the flat section.

First claim

What is claimed is:

1 . A gas turbine engine, comprising:
an impeller configured to rotate about an axis; a combustor in fluid communication with the impeller; and an inflow radial turbine aft of the impeller and in fluid communication with the combustor, the inflow radial turbine comprising a rotor with a bore having a flat bore end configured to rotate about the axis.

2 . The gas turbine engine of claim 1 , further comprising a radial section aft of the flat bore end.

3 . The gas turbine engine of claim 2 , wherein a radius of curvature of the radial section plus a radius of the flat bore end equals a radius of the bore.

4 . The gas turbine engine of claim 3 , wherein the radius of curvature of the radial section is 0.54 to 0.56 times the radius of the bore.

5 . The gas turbine engine of claim 3 , wherein the radius of the flat bore end is 0.44 to 0.46 times the radius of the bore.

6 . The gas turbine engine of claim 3 , wherein a ratio of the radius of curvature of the radial section over the radius of the flat bore end is 1.174 to 1.273.

7 . The gas turbine engine of claim 3 , wherein the radius of curvature of the radial section is greater than the radius of the flat bore end.

8 . The gas turbine engine of claim 3 , wherein the radial section is tangentially continuous with the flat bore end.

9 . The gas turbine engine of claim 3 , wherein the radial section extends through an arc of 90 degrees.

10 . A radial turbine, comprising:
a rotor configured to rotate about an axis; and a bore defined by a proximal portion of the rotor and having a flat bore end at a forward portion of the bore and a bore opening at an aft portion of the bore.

11 . The radial turbine of claim 10 , wherein the bore is symmetric about the axis.

12 . The radial turbine of claim 10 , wherein the bore comprises a radial section aft of the flat bore end.

13 . The radial turbine of claim 12 , wherein the bore further comprises a cylindrical section aft of the radial section.

14 . The radial turbine of claim 12 , wherein a radius of curvature of the radial section and plus radius of the flat bore end equals a radius of the bore.

15 . The radial turbine of claim 12 , wherein a radius of curvature of the radial section is 0.54 to 0.56 times a radius of the bore.

16 . The radial turbine of claim 12 , wherein a radius of the flat bore end is 0.44 to 0.46 times a radius of the bore.

17 . The radial turbine of claim 12 , wherein a ratio of a radius of curvature of the radial section over a radius of the flat bore end is 1.174 to 1.273.

18 . A rotor, comprising:
a disk configured to rotate about an axis; and a bore partially through the disk along the axis, wherein the bore comprises a flat section extending radially from the axis and a curved section aft of the flat section.

19 . The rotor of claim 18 , wherein a radius of curvature of the curved section is 0.54 to 0.56 times a radius of the bore.

20 . The rotor of claim 18 , wherein a radius of the flat section is 0.44 to 0.46 times a radius of the bore.

Assignees

• United Technologies Corp

Inventors

• Duong Loc Quang
• Hu Xiaolan
• Barkley Robert O
• Yang Gao

Classifications

• F01D5/04

  for radial-flow machines or engines · CPC title

• F02C6/12

  Turbochargers, i.e. plants for augmenting mechanical power output of internal-combustion piston engines by increase of charge pressure · CPC title

• F01D5/12

  Blades ({specially adapted for radial flow machines or engines F01D5/04}; blade roots F01D5/30; rotors with blades adjustable in operation F01D7/00; stator blades F01D9/02) · CPC title

• F02C3/04 Primary

  having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) · CPC title

• F01D5/027 Primary

  Arrangements for balancing (for balancing rotating bodies in general F16F15/32; for compensating imbalance G01M1/36) · CPC title