Rotor of an axial compressor stage of a turbomachine

Patent metadata

Field	Value
Publication number	US-9512727-B2
Application number	US-201213431408-A
Country	US
Kind code	B2
Filing date	Mar 27, 2012
Priority date	Mar 28, 2011
Publication date	Dec 6, 2016
Grant date	Dec 6, 2016

Abstract

The present invention relates to a rotor of an axial compressor stage of a turbomachine featuring a rotor assembly with a rotary axis, forming on its circumference a blade ring with a radially outer ring surface, and several rotor blades arranged on the blade ring. It is provided that the ring surface between two adjacent rotor blades has at least in a partial area a changing radius relative to the rotary axis of the rotor assembly both in the axial direction and in the circumferential direction.

First claim

What is claimed is:

1. A rotor of an axial compressor stage of a turbomachine, comprising:
a rotor assembly including a rotary axis, a circumference, and a blade ring with a radially outer ring surface formed on the circumference, and
a plurality of rotor blades arranged on the blade ring,
wherein the ring surface has at least in an area between two adjacent rotor blades of the plurality of rotor blades, a changing radius relative to the rotary axis of the rotor assembly both in an axial direction and in a circumferential direction;
wherein, in the area between two adjacent rotor blades, the ring surface is shaped to have a resultant surface line including a concave depression positioned toward an axially front face of the blade ring transitioning to a convex bulge positioned toward an axially rear face of the blade ring;
wherein, the convex bulge includes a peak spaced circumferentially apart from both a suction side surface of one of the two adjacent rotor blades and an opposing pressure side surface of another of the two adjacent rotor blades, the peak positioned closer to the suction side surface;
wherein, in the area between two adjacent rotor blades where the ring surface is shaped with the concave depression and the convex bulge, a second surface line of a section through the blade ring in a plane normal to the rotary axis conforms to a mathematical function including at least one chosen from: a sine function, a cosine function and a combination of sine and cosine functions;
wherein, in the area between two adjacent rotor blades, every section through the blade ring in a further plane normal to the rotary axis has a surface line defined by at least one chosen from: a sine function, a cosine function and a combination of sine and cosine functions.

2. The rotor in accordance with claim 1 , wherein for at least one section through the blade ring in a plane normal to the rotary axis, a resulting surface line in the area between two rotor blades has at least in some sections a steadily changing radius.

3. The rotor in accordance with claim 1 , wherein for at least one section through the blade ring in a plane normal to the rotary axis, a resulting surface line in the area between two rotor blades is asymmetrical.

4. The rotor in accordance with claim 3 , wherein the ring surface between the two adjacent rotor blades is shaped to have higher radii adjoining a suction side of one of the two adjacent rotor blades than adjoining a pressure side of another of the two adjacent rotor blades.

5. The rotor in accordance with claim 1 , wherein for at least one longitudinal section through the blade ring, a resulting surface line between an axially front face and an axially rear face has at least in some sections a steadily changing radius.

6. The rotor in accordance with claim 1 , wherein a course of a radius of the ring surface is parameterized by at least one chosen from an amplitude and a phase position of a trigonometric function or of several trigonometric functions superimposed one over another, with values for the amplitude and the phase position depending on a circumferential angle and axial position.

7. The rotor in accordance with claim 6 , wherein not more than five trigonometric functions are used for the definition of the three-dimensional contour of the ring surface.

8. The rotor in accordance with claim 1 , wherein the blade ring on an axially front face and/or an axially rear face has a circular shape.

9. The rotor in accordance with claim 1 , wherein the ring surface between all rotor blades of the rotor has a same three-dimensional contour.

10. The rotor in accordance with claim 1 , wherein the rotor assembly is designed as a disk with rotor blades attached thereto.

11. The rotor in accordance with claim 1 , wherein the rotor assembly is designed as a BLISK with rotor blades being configured in one piece with the rotor assembly.

12. The rotor in accordance with claim 1 , wherein the concave depression is positioned nearer the suction side surface than the pressure side surface.

13. The rotor in accordance with claim 1 ,
wherein for at least one longitudinal section through the blade ring, a resulting surface line between an axial start value and an axial end value has a steadily changing radius, and wherein the axial start value, in the axial direction, is positioned upstream of leading edges of the rotor blades and wherein the axial end value, in the axial direction, is positioned downstream of trailing edges of the rotor blades; and
wherein the ring surface between the axial start value and the downstream leading edges of the rotor blades, and also between the trailing edges of the rotor blades and the downstream axial end value, includes the changing radius relative to the rotary axis in the circumferential direction.

14. The rotor in accordance with claim 1 , wherein a third surface line of a section through the blade ring in a plane normal to the rotary axis at the convex bulge and a fourth surface line of a section through the blade ring in a plane normal to the rotary axis at the concave depression conform to a mathematical function including at least one chosen from: a sine function, a cosine function and a combination of sine and cosine functions.

Assignees

• Johann Erik
• Heinichen Frank
• Rolls Royce Deutschland Ltd & Co Kg

Inventors

• Johann Erik
• Heinichen Frank

Classifications

• F05D2250/711

  convex · CPC title

• F01D5/34

  Rotor-blade aggregates of unitary construction {, e.g. formed of sheet laminae; (discs formed of sheet laminae F01D5/028; ceramic materials F01D5/284, composite materials F01D5/282)} · CPC title

• F05D2250/73

  asymmetric · CPC title

• F01D5/143 Primary

  Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour · CPC title

• Y02T50/673

  Cross-Sectional Technologies · mapped topic