Guide vane ring ,guide vane, inner ring and turbomachine

• US 20150275683A1
• Filed: 03/30/2015
• Published: 10/01/2015
• Est. Priority Date: 03/31/2014
• Status: Active Grant

• Current Assignee: MTU Aero Engines AG (MTU)
• Original Assignee: MTU Aero Engines AG (MTU)
• Inventors: Humhauser, Werner, Klingels, Hermann
• Granted Patent: US 10,364,827 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: F01D 1/02 with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbinesF01D1/24 takes precedence; without stationary working-fluid guiding means F01D1/18
• 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 25/16 Arrangement of bearings; Supporting or mounting bearings in casings bearings per se F16C
• CPC Class Codes: F01D 7/00 Rotors with blades adjustable in operation; Control thereof for reversing F01D1/30
• CPC Class Codes: F01D 9/041 using blades F01D5/148 takes precedence
• CPC Class Codes: F04D 29/083 especially adapted for elastic fluid pumps
• CPC Class Codes: F04D 29/321 for axial flow compressors
• CPC Class Codes: F04D 29/563 specially adapted for elastic fluid pumps
• CPC Class Codes: F05D 2220/30 in turbines
• CPC Class Codes: F05D 2220/32 in gas turbines
• CPC Class Codes: F05D 2230/90 Coating; Surface treatment manufacture with deposition of material F05D2230/30
• CPC Class Codes: F05D 2240/12 Fluid guiding means, e.g. vanes
• CPC Class Codes: F05D 2240/56 Brush seals
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

An adjustable guide vane ring of a turbomachine having an inner ring, the guide vanes of which each have a radially inner vane disk with disk thickness increasing in the direction of flow and acting as a bearing pin; a guide vane, as well as an inner ring for such a guide vane ring, as well as a turbomachine are disclosed.

Claims

1. An adjustable guide vane ring (1) of a turbomachine (2), with a plurality of guide vanes (4) forming a row of guide vanes and with an inner ring (6) for stabilizing the row of guide vanes, wherein the guide vanes (4) each have a radially outer adjusting pin relative to a lengthwise axis of the guide vane ring for interacting with an adjusting means, and wherein the guide vanes (4), each with a radially inner valve disk (14), are taken up in bearing recesses (26) of the inner ring (6), wherein the radially inner valve disks (14) act as bearing pins, whereby they and/or the bearing recesses (26) are coated on their bearing surfaces (36, 38, 40), and the vane parts (10) have an overhang on the side of the back edge, and the radial height of the vane disks increases downstream of a primary flow.

2. The adjustable guide vane ring according to claim 1, wherein the radial height of the vane disk (14) upstream amounts to between 15% and 30% of its diameter.

3. The adjustable guide vane ring according to claim 1, wherein the radially inner vane disks (14) have a cylindrical bearing surface over their radial height.

4. The adjustable guide vane ring according to claim 1, wherein the vane disks (14) are distanced from the base (36) of the bearing recesses (26).

5. The adjustable guide vane ring according to claim 1, wherein the inner ring (6) is divided axially and has a front ring segment (22) and a back ring segment (24), in which the bearing recesses (26) are formed as halves in each case.

6. The adjustable guide vane ring according to claim 5, wherein the ring segments (22, 24) each have at least one flange (28, 30) displaced radially inward relative to the bearing recesses, (26) for joining the segments together.

7. The adjustable guide vane ring according to claim 5, wherein the back ring segment (24) has downstream an end section (50) directed radially inward from a segment surface (48) on the side of the primary flow.

8. The adjustable guide vane ring according to claim 7, wherein a radial gap between the end section (50) and an opposite-lying rotor section (20) is closed by a sealing device (52).

9. The adjustable guide vane ring according to claim 8, wherein the sealing device (52) is secured in position by means of a retaining ring (54) disposed on the inner ring (4).

10. The adjustable guide vane ring according to claim 5, wherein the front ring segment (22) has an upstream projection (68) for axial overlapping a body section (70) of an upstream row of rotating blades (72) of the turbomachine (2).

11. The adjustable guide vane ring according to claim 1, wherein a secondary flow injection extends through the inner ring (6), this flow exiting from at least several of the vane disks on the intake side and/or the discharge side.

12. The adjustable guide vane ring according to claim 1, wherein at least several vane disks (14) have a hollow space (44).

13. The adjustable guide vane ring according to claim 1, wherein the adjustable guide vane ring is employed in a turbomachine (2).

14. (canceled)

15. (canceled)