GUIDE VANE RING FOR A TURBOMACHINE

• US 20170314406A1
• Filed: 04/26/2017
• Published: 11/02/2017
• Est. Priority Date: 04/28/2016
• Status: Active Grant

• Current Assignee: MTU Aero Engines AG (MTU)
• Original Assignee: MTU Aero Engines AG (MTU)
• Inventors: Wolf, Hannes, Halcoussis, Alexander
• Granted Patent: US 10,677,076 B2
• Time in Patent Office: Days
• CPC Class Codes: F01D 17/162 for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line F01D17/167 takes precedence
• CPC Class Codes: F01D 5/143 Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
• CPC Class Codes: F01D 9/041 using blades F01D5/148 takes precedence
• CPC Class Codes: F04D 29/542 Bladed diffusers fixing blades to stators F01D9/042
• CPC Class Codes: F04D 29/563 specially adapted for elastic fluid pumps
• CPC Class Codes: F04D 29/681 especially adapted for elastic fluid pumps
• CPC Class Codes: F05D 2220/32 in gas turbines
• CPC Class Codes: F05D 2250/314 the axes being inclined in relation to each other
• CPC Class Codes: F05D 2250/61 corrugated
• CPC Class Codes: F05D 2250/711 convex
• CPC Class Codes: F05D 2250/712 concave
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A guide vane ring for a turbomachine minimizes a leakage flow that passes through a recess (11) into which a guide vane disk is inserted. It has a guide vane row having a plurality of guide vanes (20), each having a vane airfoil (24) and a vane disk (21), as well as an inner ring (10) having an inner ring surface (12) facing the plurality of guide vanes. Viewed in the direction (R) of a designated primary flow streaming through the turbomachine, the vane disks (21) have a front and a rear surface region (22a, 22b). In a nominal and/or a maximum open position of the guide vanes, the front and/or the rear surface region (22a, 22b) of at least one of the vane disks has an offset (31a, 31b) from the inner ring surface (12) that is radially disposed (relative to a central axis (X) of the inner ring (10)).

Claims

1. A guide vane ring for a turbomachine, the guide vane ring comprising:

a guide vane row having a plurality of pivotably mounted guide vanes, each having a vane airfoil and a vane disk;

an inner ring having an inner ring surface facing the plurality of guide vanes;

viewed in a direction of a designated primary flow streaming through the turbomachine, the vane disks having a front and a rear surface region, wherein, in a nominal or a maximum open position of the guide vanes, the front or rear surface region of at least one of the vane disks has an offset from the inner ring surface radially disposed relative to a central axis of the inner ring.

2. The guide vane ring as recited in claim 1 wherein the front surface region of the vane disk in the nominal or the maximum open position of the guide vanes is sunken relative to the inner ring surface.

3. The guide vane ring as recited in claim 2 wherein the offset between the front surface region and the inner ring surface has a height 3% to 15% of the diameter of the vane disk or of a channel height.

4. The guide vane ring as recited in claim 1 wherein the rear surface region of the vane disk in the maximum open position of the guide vanes is raised relative to the inner ring surface.

5. The guide vane ring as recited in claim 4 wherein the offset between the rear surface region and the inner ring surface has a height 3% to 15% of the diameter of the vane disk or of a channel height.

6. The guide vane ring as recited in claim 1 wherein in the nominal or maximum open position of the guide vanes, the front and the rear surface region have an offset of a same height from the inner ring surface.

7. The guide vane ring as recited in claim 1 wherein at a side facing the vane airfoil thereof, the at least one vane disk having a plane, a convex, a concave or a corrugated surface.

8. An assembly for the guide vane ring as recited in claim 1, the assembly having the inner ring and at least one guide vane insertable into a recess of the inner ring.

9. A turbomachine comprising the guide vane ring as recited in claim 1.