DE102019219273A1 - METHOD OF MEASURING A COMPONENT OF A FLOW MACHINE - Google Patents

Abstract

The present invention relates to a method for measuring a first component (21.1) of a turbomachine (1), in which method - a first recording (41) of the first component (21.1) is created (61); - on the basis of the first recording (41) a possible damaged area (23) is identified (62) in an area (35) of the first component (21.1); - a second recording (42) of the first component (21.1) is made (63), namely of the area (35) with a resolution greater than that of the first recording (41); wherein the first and the second recording (41, 42) are created using different measuring methods.

Description

Technical area

The present invention relates to a method for measuring a component of a turbomachine.

State of the art

An axial flow machine is functionally divided into a compressor, combustion chamber and turbine, whereby in the case of an aircraft engine, air sucked in is compressed in the compressor and burned in the downstream combustion chamber with added kerosene. The resulting hot gas, a mixture of combustion gas and air, flows through the downstream turbine and is expanded in the process. As a rule, the turbine and the compressor each have a multi-stage design, each stage comprising a stator and a rotor. The stators and rotors are each made up of a plurality of consecutive blades around which the compressor or hot gas flows, depending on the application.

In the case of an aircraft engine, damage can occur in the course of use, i.e. damage to its components. The components arranged in the gas duct, for example blades, but also gas duct plates, etc., can be particularly endangered and safety-relevant. The damaged areas can be caused by particles hitting at a comparatively high speed, but also by larger objects. Even smaller damaged areas can be problematic in that they can represent an initial point for crack propagation. The detection of such damaged areas can therefore be of particular importance.

Presentation of the invention

The present invention is based on the technical problem of specifying an advantageous method for measuring a component of a turbomachine.

This is achieved according to the invention with the method according to claim 1. In this case, a first recording is first made of the component (“first component”), on the basis of which an area of the first component is determined in which a possible damaged area is arranged. A second image is then taken of this area, using a different measuring method than the first image and with a higher resolution.

An advantage can e.g. B. lie in the fact that the second recording offers a high level of accuracy, so the damaged area is measured very precisely. This can be advantageous, for example, with regard to later processing, see in detail below. On the other hand, the entire component is or does not have to be recorded with a correspondingly high level of accuracy, which reduces the measurement time and can therefore also have economic advantages (shortened revision times, etc.). As will become clear below, the present method can be automated well, so that a largely autonomous damage detection can be defined.

Preferred refinements can be found in the dependent claims and the entire disclosure, with the presentation of the features not always distinguishing in detail between process and use or device aspects; in any case, the disclosure is to be read implicitly with regard to all claim categories.

The recordings contain pixel-related information about the component, with the (selected) area being recorded with more pixels in the second recording than in the first recording. Accordingly, the information about the possible damaged area is available in the second image with a larger number of pixels. Not only is it “zoomed in”, but different measurement methods are used. As mentioned, this can be advantageous in terms of the desired combination of speed and accuracy. At least one of the measuring methods is preferably a 3D measuring method, that is to say the corresponding recording contains distance information as a function of the pixel.

According to a preferred embodiment, the second recording is created as a 3D recording, preferably in a confocal-chromatic measuring method. This can e.g. B. because of a comparatively good resistance to glossy surfaces, so a stable measurement in this regard can be an advantage. In addition, a particularly precise image of the area or the damaged area can be created. Alternatively, a strip projection is also possible, for example, in which case the 3D distance information can be determined from the curvature of the lines.

In a preferred embodiment, the first recording is a photo-realistic, that is to say true-color recording. This can e.g. B. be of interest with regard to the evaluation or documentation of thermomechanical conditions or deposits. As an alternative or in addition, it can preferably be a 3D image; the distance or space information can be, for. B. can be used when positioning the receiving unit for the second recording and / or for a later tool positioning, see below.

In general, the first recording can also be made, for example, with a 3-D phase shift measurement or a scanning laser measurement, but a 3-D stereo measurement method is preferably used. This can be advantageous because of the high measuring speed, with any accuracy deficit being compensated for with the second recording.

According to a preferred embodiment, in addition to the first component, a first recording is also made of a second component (the overview recording). There is therefore also a picture of the second component with a coarser resolution, which can be created correspondingly quickly (see above). The term “recording” should not necessarily imply a separate file or a separate image; the first images of the components can, for example, also be created at the same time in the form of an overview image. However, the first recordings of the components are preferably made one after the other, also in view of limited accessibility. Regardless of whether they are recorded successively or together, the first recordings are made using the same measuring method, for example with a 3D stereo measurement.

The first and second components are structurally identical, so they have the same shape and size, for example. The area which is then measured in detail with the second recording can then advantageously be determined or identified by comparing the first recordings. This can, in contrast to a comparison with an ideal target or initial state, for. B. to the effect that it can be used to filter out even component wear. A distinction can be made between, on the one hand, that wear that occurs as standard during operation and causes a uniform change (from component to component) and, on the other hand, locally invasive damage, e.g. due to particle impact, etc.

In a preferred embodiment, a 3D image (overview image) is created in the first step of a large number of structurally identical components of the turbomachine or the aircraft engine. “Large number” means at least 3, preferred are at least 5 , 7th or 9 (with possible upper limits of, for example, a maximum of 300, 200 or 150). Each 3D recording contains distance information from the respective component, i.e. information on its three-dimensional surface profile. A relief is therefore available for each component, namely 3D information on a surface area.

These reliefs are summarized in the course of a mean value calculation, an averaged component relief is created. If, for example, one of the components has a damaged area at a point x / y, this will also adversely affect the averaging. However, since the larger number of components there has no damage on a statistical average, the deviation of the averaged component relief from an “averaged component relief without damage” will be less than the deviation of the damaged component from the averaged component relief. The damaged component can be identified by comparing it with the averaged component relief.

The variants described in the preceding paragraphs “comparison of first recordings of structurally identical components” and in particular “comparison with averaged component relief” are also considered to be an invention regardless of the main claim combination of two different measuring methods and / or second recordings with higher resolution and should be disclosed accordingly.

As already mentioned, the component or components are preferably arranged in the gas duct of the turbomachine, that is to say that the compressor or hot gas flows around them during operation. In a preferred embodiment, the measurement takes place in the assembled state, so the components advantageously do not have to be removed. Instead, a receiving unit is inserted into the gas duct as a probe. Different measuring or microscope heads can be integrated into such a probe, but the individual heads can also be introduced one after the other with their own probe.

In a preferred embodiment, the components are blades, preferably a component relief is created from blades arranged together on a ring, preferably an averaged relief of the blade leading edges.

As already mentioned, the turbomachine is preferably an aircraft engine. The method discussed here can preferably take place in the fully assembled state of the aircraft engine, in particular when it is mounted on the aircraft. In general, an application in the turbine area is also conceivable; components of the compressor are preferably measured, in particular its blades (e.g. rotor blades).

The invention also relates to a method for processing the first component, that is to say the possible damaged area, a tool path (movement path) being created on the basis of the first and / or second recording. With the help of this tool path, a tool is guided along the component and the damaged area is removed, for example by removing material, e.g. B. by grinding etc.

The invention also relates to a measurement setup with a turbomachine, a Recording unit and a control unit. As described above, the recording unit has measuring or microscope heads, e.g. B. for a 3D stereo measuring method (first recordings) and a confocal chromatic measuring method (second recording). The control unit is set up to carry out the method discussed above, that is, it causes the recording unit to record the first recording (s) and identifies a possibly critical area in this or on the basis of this (preferably by averaging, see above). On the basis of this, it causes the recording unit to then take the second recording with a higher resolution.

The invention also relates to a computer program product which has commands which, when executed by a control unit of such a knife assembly, cause the latter to carry out the described method steps.

Figure list

The invention is explained in more detail below with the aid of an exemplary embodiment, with the individual features within the framework of the independent claims also being essential to the invention in other combinations and furthermore no individual distinction is made between the different claim categories.

• 1 eine Strömungsmaschine, nämlich ein Flugtriebwerk in einem schematischen Axialschnitt;
• 2 einen Ausschnitt eines Schaufelkranzes in einer Axialansicht;
• 3 das erfindungsgemäße Vorgehen am Beispiel einer Schaufel in einer Seitenansicht;
• 4 die Ermittlung einer Schadstelle durch einen Abgleich einer 3D Aufnahme mit einem gemittelten Bauteilrelief.
• 5 das erfindungsgemäße Verfahren in einem Ablaufdiagramm.

Shows in detail

• 1 a flow machine, namely an aircraft engine in a schematic axial section;
• 2 a section of a blade ring in an axial view;
• 3rd the procedure according to the invention using the example of a shovel in a side view;
• 4th the determination of a damaged area by comparing a 3D image with an averaged component relief.
• 5 the method according to the invention in a flowchart.

Preferred embodiment of the invention

1 shows a turbomachine 1 , specifically a turbofan engine, in an axial section. The turbo machine 1 is functionally divided into compressors 1a , Combustion chamber 1b and turbine 1c . Both the compressor 1a as well as the turbine 1c are each made up of several stages. Each of the stages consists of a stator 5 and a rotor 6th together. The reference number 7th refers to the gas channel, i.e. the compressor gas channel in the case of the compressor 1a or the hot gas duct in the case of the turbine 1c . The air that is sucked in is compressed in the compressor gas duct and is then transferred to the downstream combustion chamber 1b burned with added kerosene. The hot gas flows through the hot gas duct and drives the rotors in the process 6th around the axis of rotation 2 rotate.

2 illustrates in a schematic representation several in a gas duct 7th arranged components 21 , namely shovels. Together these form a blade ring 22nd , of which only one segment is shown. On a first component 21.1 there is a damaged area 23 , in this case a leading edge area damaged by particle impact.

3rd illustrates the measurement of the first component 21.1 in detail, it shows the shovel 30th in a side view ( 2 however in an axial view). The shovel 30th has a leading edge 30.1 and a trailing edge 30.2 , the measurement is done from the front, so it will be the front edge 30.1 pictured.

Here there is a recording unit 31 Application that a first recording head 31.1 and a second pickup head 31.2 having. With the first recording head 31.1 the first step is a first recording 41 created, namely an overview recording. In the present case, the first measurement method is a 3D stereo measurement with which this overview image can be created in a short time.

Based on the first recording 41 then becomes an area 35 identified in which the damaged area 23 lies. Then the second recording head is used 31.2 a second shot 42 of the area 35 created, which depicts this with a comparatively higher resolution. Would the entire scoop 30th with the second recording head 31.2 sampled, the measurement duration would not be economically feasible. By combining it with the first recording 41 can accurately measure the damaged area 23 can be achieved in connection with an overall shortened measurement duration. With the second recording head 31.2 In the present case, it is a confocal-chromatic measuring head. The recording unit 31 is controlled by a control unit 59 controlled.

In the course of measuring the blade ring 22nd is made by every component 21 , so every shovel a first shot 41 created. Based on these recordings, each of the leading edge 30.1 of the respective shovel 30th will show an averaged component relief 45 created, cf. 4th . Since the blades are in the present case, this is an averaged relief of their leading edges 30.1 . 4th shows the distance values d plotted against the position x and also illustrates a relief 46 from the first shot 41 of the first component 21.1 , i.e. the shovel with the damaged area 23 . This can be determined based on the deviation from the averaged component relief 45 detect well.

5 illustrates some steps of the method according to the invention in a flowchart. In a first step 51 becomes the first recording 41 created 61 . Then in a second step 52 the area 35 identified 62 . In a third step 53 becomes the second shot 42 of the area 35 created 63 . Are preferred in the first step 51 further first recordings 41 from the other components 21 created 71 and is based on the entire first recordings 41 in the second step 52 first the component relief 45 created 72 . This then becomes the area 35 identified 62 .

List of reference symbols

1

Turbo machine

1a

compressor

1b

Combustion chamber

1c

turbine

2

Axis of rotation

5

stator

6th

rotor

7th

Gas duct

21

Components

21.1

First component

21.2

Second component

22nd

Blade ring

23

Damaged area

30th

shovel

30.1

Leading edge

30.2

Trailing edge

31

Recording unit

31.1

First recording head

31.2

Second recording head

35

Area

41

First shot

42

Second shot

45

Component relief (averaged)

46

relief

51

First step

52

Second step

53

Third step

59

Control unit

61

Creation of a first recording of the first component

62

Identification of the area

63

Take a second shot of the area

71

Creation of the first recordings of a large number of components

72

Creation of the averaged component relief

Claims (15)

Method for measuring a first component (21.1) of a turbomachine (1) with at least the following steps: - Creating (61) a first receptacle (41) of the first component (21.1); - Identifying (62) a possible damaged area (23) on the basis of the first recording (41) and defining an area (35) of the first component (21.1) in which the identified damaged area (23) is located; - Creating (63) a second recording (42) of the defined area (35) of the first component (21.1) with a greater resolution than the first recording (41). Procedure according to Claim 1 , wherein the first and the second recording (41, 42) are created with different measuring or recording methods. Procedure according to Claim 1 or 2 , in which at least one of the recordings (41, 42) is created as a 3D image (61, 63), in particular in which the second image (42) is created as a 3D image using a confocal chromatic measuring method (63). Method according to one of the preceding claims, in which the first recording (41) is a photo-realistic, that is to say true-color recording. Method according to one of the preceding claims, in which the first recording (41) is created as a 3D recording (61) in a 3D stereo measurement method. Method according to one of the preceding claims, in which, in addition, of a second component (21.2) of the turbomachine (1), which is structurally identical to the first component (21.1), a first Recording (41) is created (71), the area (35) of the first component (21.1) from which the second recording (42) is created (63) being identified by comparing the first recordings (41). Method according to one of the preceding claims, in which a first receptacle (41) is created (71) from a plurality of components (21) of the turbomachine (1) that are identical to the first component (21.1), the first receptacles (41) are created as 3D recordings and an averaged component relief (45) is created (72) from the 3D recordings of the components (21). Procedure according to Claim 7 , in which the area (35) of the first component (21.1) from which the second recording (42) is created is identified by comparing the first recording (41) of the first component (21.1) with the averaged component relief (45) . Method according to one of the preceding claims, in which the first component (21.1) or the components (21) are arranged in a gas duct (7) of the turbomachine (1), a receiving unit (31) for creating the receptacles (41, 42 ) is introduced into the gas channel (7). Method according to one of the preceding claims, in which the first component (21.1) or the components (21) is a blade (30) or are blades (30) which are received with the receptacles (41, 42) axially from the front . Procedure according to Claim 10 combined with Claim 7 or 8th , in which the plurality of components (21) are blades (30) arranged together on a blade ring (22) and the averaged component relief (45) is an averaged relief of their front edges (30.1). Method according to one of the preceding claims, in which the turbomachine (1) is an aircraft engine. Method for processing a first component (21.1) of a turbomachine (1), in which the component (21.1) is measured in a method according to one of the preceding claims, wherein the first and / or second receptacle (41, 42) is also used first component (21.1) a tool path for automated post-processing of the damaged area (23) is created. Measurement setup, with - A turbomachine (1), in particular an aircraft engine or module thereof, which has a first component (21.1); - A recording unit (31) which is designed to create recordings (41, 42) using different measuring methods; and - a control unit (59); wherein the control unit (59) is set up to - to create a first receptacle (41) of the first component (21.1) by means of the receiving unit (31); - using the first receptacle (41) in an area (35) of the first component (21.1) to identify any damaged area (23); - using the recording unit (31) to create a second recording (42) of the first component (21.1) with a different measuring method, namely of the area (35) with a greater resolution than the first recording (41). Computer program product which has commands which, when executed by a control unit (59), of a measurement setup according to Claim 14 cause these to - create a first receptacle (41) of the first component (21.1) by means of the receiving unit (31); - using the first receptacle (41) in an area (35) of the first component (21.1) to identify any damaged area (23); - using the recording unit (31) to create a second recording (42) of the first component (21.1) with a different measuring method, namely of the area (35) with a greater resolution than the first recording (41).

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