Turbomachine stage and method for determining a seal gap and/or an axial position of such a turbomachine stage

Patent metadata

Field	Value
Publication number	US-9957833-B2
Application number	US-201414284116-A
Country	US
Kind code	B2
Filing date	May 21, 2014
Priority date	May 22, 2013
Publication date	May 1, 2018
Grant date	May 1, 2018

Abstract

A turbomachine stage, particularly a turbine stage or a compressor stage of a gas turbine, is disclosed. The turbomachine stage has a, conical in particular, housing in which is arranged a moving vane arrangement with multiple moving vanes which have an exterior shroud band with at least one radial sealing flange. The sealing flange has a recess arrangement with at least one radial recess in which, centrally in particular, a radial projection is arranged. There is arranged on the housing a sensor arrangement with at least one capacitive sensor for detecting a radial clearance to a peripheral surface of the sealing flange.

First claim

What is claimed is:

1. A turbomachine stage, comprising:
a housing having an external surface;
a moving vane arrangement disposed within the housing, wherein the moving vane arrangement disposed along an axial rotation axis and including at least one radially disposed vane disposed along a radial axis transverse to the axial rotation axis, the at least one vane having an exterior shroud band section including a sealing flange, the sealing flange having a recess arrangement including a radial recess and a radial projection, that together, define a peripheral surface of the sealing flange; and
a sensor arrangement including a sensor having a sensing surface, the sensor arrangement being arranged on the housing so that the sensing surface of the sensor positionally converges towards or positionally diverges away in a direction relative to the radial axis in a direction that is different from the direction of the radial axis, and the converging or the diverging sensing surface of the sensor and the peripheral surface of the sealing flange, in combination, further define a radial clearance therebetween, and a radial distance of the radial clearance is detectable by the positionally converged or the positionally diverged sensor.

2. The turbomachine stage according to claim 1 , wherein the turbomachine stage is a turbine stage or compressor stage of a gas turbine.

3. The turbomachine stage according to claim 1 , wherein the sensor arrangement has a second sensor and a third sensor, wherein sensing surfaces of the second sensor and the third sensor form counter-directional, essentially equally sized angles with an axis of rotation of the turbomachine stage.

4. The turbomachine stage according to claim 1 , wherein the peripheral surface of the sealing flange associated with the radial projection is radially spaced radially outbound from the peripheral surface of the sealing flange disposed adjacent to the radial recess.

5. The turbomachine stage according to claim 1 , further comprising a processor coupled to the sensor arrangement.

6. A method for determining one or both of a radial distance and an axial position of a seal gap between a sealing flange of a moving vane arrangement and a housing in a turbomachine stage, the moving vane arrangement disposed along an axial rotation axis and having at least one vane disposed along a radial axis that is transverse to the axial rotation axis, wherein the sealing flange has a recess arrangement with a radial recess and a radial projection and wherein a sensor arrangement with a sensor has a sensing surface and is arranged on the housing so that the sensing surface of the sensor positionally converges towards or positionally diverges away in a direction relative to the radial axis that is different from the direction of the radial axis, comprising the steps of:
detecting the radial recess and the radial projection of the recess arrangement by the positionally converged or the positionally diverged sensor;
generating a signal swing representative of the detected radial recess and the radial projection by the positionally converged or the positionally diverged sensor; and
determining the radial distance of the seal gap at least in part from the generated signal swing.

7. The method according to claim 6 , further comprising the step of assigning the signal swing to the radial distance of the moving vane arrangement based on a prior calibration.

8. The method according to claim 7 , further comprising the steps of:
detecting a second signal swing of the sensor arrangement as a result of the radial recess and the radial projection being detected by the sensor of the sensor arrangement; and
assigning the signal swing and the second signal swing to an axial position of the moving vane arrangement based on a prior calibration.

9. The method according to claim 7 , further comprising the steps of:
detecting a second signal swing of the sensor arrangement as a result of the radial recess or the radial projection being detected by the positionally converged or the positionally diverged sensor of the sensor arrangement; and
assigning a width of the second signal swing to an axial position of the moving vane arrangement based on a prior calibration.

10. The method according to claim 7 , further comprising the step of detecting a rubbing on the housing opposite from the sealing flange.

Assignees

• MTU Aero Engines AG

Inventors

• Gerbl Florian
• Gruendmayer Juergen
• Stadlbauer Martin
• Trassl Ernst

Classifications

• F01D21/003 Primary

  Arrangements for testing or measuring (for measuring vibrations G01H) · CPC title

• F01D11/14

  Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing (rotors with blades adjustable in operation F01D7/00) · CPC title

• F05D2270/821

  Displacement measuring means, e.g. inductive · CPC title

• F01D17/02

  Arrangement of sensing elements · CPC title

• G01B7/14

  for measuring distance or clearance between spaced objects or spaced apertures (G01B7/30 takes precedence) · CPC title