DE102020200664A1 - Method for repairing a sealing air device for a turbo machine, sealing air device and turbo machine with a sealing air device - Google Patents

Abstract

The invention relates to a method for repairing a sealing air device (10) for a turbo machine (100), comprising at least the following steps: a) Providing the sealing air device which is used to seal a sealing gap (50) between two components (30, 40) of the sealing air device ( 10) is formed opposite a blocking air flow (12), wherein a first component (30) of the two components comprises a receiving area (32) with at least two projections (36, 38), between which there is a groove (34) for receiving one for sealing of the sealing gap formed sealing ring (14); b) removal of at least one damaged projection sub-area (37) of at least one first projection (36) of the at least two projections; c) arranging the sealing ring and one for supporting the sealing ring in the axial extension direction (A) of the first component formed support device (20) of the air barrier device on the first component, wherein the support device g is supported on a contact area (39) of the sealing air device in order to prevent a relative movement (RB) between the supporting device and the second projection, which is oriented away from a second projection (38) of the two projections in the axial direction of extent, and wherein the sealing ring between the supporting device and the second protrusion is arranged. Further aspects of the invention relate to a sealing air device for a turbo machine and a turbo machine.

Description

The invention relates to a method for repairing a sealing air device for a turbomachine. Further aspects of the invention relate to a sealing air device for a turbomachine and a turbomachine with such a sealing air device.

In order to prevent hot gases from getting through gaps into areas outside a main flow channel and thermally overloading components arranged in these areas when operating turbo engines, especially jet engines, a targeted flow of so-called sealing air, also referred to below as sealing air flow, is used. It is customary, for example, to seal oil-carrying pipelines through bearing structures or generally support structures with sealing rings, which can also be referred to as piston rings or “piston rings”, against undesired leakage of the sealing air.

The sealing rings are wearing parts and can fail over time during operation of the turbomachine. If a sealing ring fails, it sometimes also breaks and consequently damage or at least partial breakage of a receiving geometry receiving the sealing ring.

The object of the present invention is to provide a method for repairing a sealing air device, a sealing air device and a turbo-engine of the type mentioned in which, particularly in the event of a sealing ring failure, a sealing gap can be sealed with little effort.

According to the invention, this object is achieved by a method with the features of claim 1, by a sealing air device with the features of claim 12 and by a flow machine with the features of claim 14. Advantageous configurations with expedient developments of the invention are specified in the respective subclaims.

A first aspect of the invention relates to a method for repairing a sealing air device for a turbo machine. In a step a) of the method, the air barrier device is provided, which is designed to seal a sealing gap between two components of the air barrier device against a flow of barrier air, a first component of the two components comprising a receiving area with at least two projections, between which there is a groove for Receiving a sealing ring designed to seal the sealing gap extends. In a step b) of the method, at least one damaged projection sub-area of at least one first projection of the at least two projections is removed. In a step c) of the method, the sealing ring and a supporting device of the sealing air device designed to support the sealing ring in the axial extension direction of the first component are arranged on the first component, the supporting device being supported on a contact area of the sealing air device by a second in the axial extension direction Projection of the two projections away-oriented relative movement between the support device and the second projection, and wherein the sealing ring is arranged between the support device and the second projection.

A major advantage of this method is that by removing the damaged part of the protrusion and arranging the support device and the sealing ring, the sealing air device can be repaired in a simplified manner without having to replace the first component. The support device can then take over the function of the first projection and support the sealing ring in the axial direction of extent. By removing at least the damaged projection sub-area, it is possible to effectively prevent individual parts from becoming detached from the damaged projection sub-area and being distributed in the turbomachine. In this way, any consequential damage caused by loosening the individual parts can be avoided.

The support device can preferably comprise a split repair collar and in this case also be referred to as a “split repair collar”. In its arrangement on the first component, the support device can extend over a projection area in the axial direction of extension instead of the projection sub-area, preferably instead of the first projection. The projection area corresponds to a zone of the first component over which the ablated projection sub-area or the first projection has previously extended in the direction of axial extension. In this way, the support device can directly take on respective functions, namely, for example, the stationary holding of the sealing ring, which were previously fulfilled by the projection sub-area or by the first projection. By removing at least the damaged part of the projection and then arranging the sealing ring and the support device, for example complex welding work to repair the first component and any replacement of the first component can be avoided. The method can accordingly lead to a more extensive dismantling of the sealing air device or the Turbo machine and a replacement of the first component can be dispensed with. As a result, the sealing air device can be repaired in the context of a short stay in an “on-wing support shop”, ie in a repair station, at which, for example, an “on-wing repair”, ie a repair of the turbomachine in its arrangement on a wing of an aircraft can be carried out.

In an advantageous development of the invention, a third projection of the first component is used as the contact area. This is advantageous because it enables the support device to be supported in the axial direction of extension with particularly little effort. As a result, it is accordingly possible to dispense with additional securing of the support device against undesired movement in the axial direction of extent. The contact area can thus form a stop for securing the support device in the axial position, that is to say, in other words, for securing a predetermined position of the support device in the direction of axial extension.

In a further advantageous development of the invention, in step b) at least the damaged projection sub-area is removed by machining the first component. This is advantageous because the exciting machining, for example by milling the first component, can result in a particularly fast and thus time-saving removal of at least the damaged projection sub-area.

In a further advantageous development of the invention, the first projection is completely removed in step b). This is advantageous because it can ensure that the support device abuts the sealing ring over a particularly large area. In addition, by completely removing the first projection, it is possible to dispense with, for example, providing a shoulder on the support device, through which the support device must overlap a remaining remainder of the first projection after the removal of the damaged projection sub-area, in order to thereby come into contact with the sealing ring come.

In a further advantageous development of the invention, the support device comprises at least two support device shells which are each arranged on the first component, as a result of which the support device shells jointly enclose the first component on the circumferential side. This is advantageous because the support device can be mounted particularly easily as a result. The at least two support device shells can in particular be axially separated from one another and thus designed as respective half-shells. During the assembly of the support device, the support device shells can each be brought up to the first component and then moved towards one another in the radial extension direction of the first component. The two support device shells can then be braced at least indirectly with the first component. In the present case, the expression indirect is to be understood as meaning that further components, for example sealing elements, can be arranged between the support device shells and the first component, which components can be clamped by the bracing of the support device shells with the first component.

In a further advantageous development of the invention, the at least two support device shells are fixed to the first component by means of at least one flexible connecting element. This is advantageous because the flexible connecting element can be adapted particularly flexibly to an external geometry of the support device. This allows the support device to be fixed to the first component in a simplified manner. The support device shells can in particular be braced to the first component by means of the at least one flexible connecting element.

In a further advantageous development of the invention, a wire is used as the flexible connecting element. This is advantageous because such a wire can be deformed particularly flexibly on the one hand and can also withstand higher temperatures on the other hand, so that the wire is particularly suitable for its use at high temperatures, as can occur when the turbo machine is in operation.

In a further advantageous development, the at least two support device shells are fixed to the first component by means of at least one screw connection. The screw connection can also be referred to as a screw connection. As a result, a particularly durable and reversibly detachable connection can be created between the support device shells and the first component.

In a further advantageous development of the invention, arranging the supporting device on the first component forms a receiving gap for receiving the sealing ring between the supporting device and the second projection, the receiving gap having at least essentially the same width in the axial direction as the groove. This is advantageous because by repairing the air barrier device, an installation position which the sealing ring has in the undamaged state of the first projection can be reproduced particularly precisely.

In a further advantageous development of the invention, when the support device is arranged in step c), at least one elastic sealing element is clamped between the support device and the first component. This is advantageous because the elastic sealing element can provide a particularly effective seal between the support device and the first component. Another advantage is that due to the elasticity of the sealing element, any tolerances in the sealing gap can be compensated for in a simple manner. The at least one elastic sealing element can be assigned to the air barrier device or the support device.

In a further advantageous development of the invention, an O-ring is used as the at least one elastic sealing element. This is advantageous because such an O-ring has a simple structure and a particularly good sealing effect can be achieved by means of the O-ring. Due to the elasticity of the O-ring, tolerances in the sealing gap, in particular in the receiving area, can be compensated for in a particularly simple manner.

A second aspect of the invention relates to a sealing air device for a turbo machine, which is designed to seal a sealing gap between two components of the sealing air device from a sealing air flow, in which a first component of the two components comprises at least one projection, the sealing air device being arranged on the first component Support device comprises and a receiving gap extends between the at least one projection and the support device, in which a sealing ring of the sealing air device designed to seal the sealing gap is received, the supporting device being designed to support the sealing ring in the axial extension direction of the first component and on a contact area of the sealing air device is supported by a relative movement between the support device and the at least one projection oriented in the axial extension direction and away from the at least one projection g to prevent, and wherein the sealing ring is arranged between the support device and the at least one projection. The features presented in connection with the method according to the invention according to the first aspect of the invention and their advantages apply accordingly to the sealing air device according to the invention according to the second aspect of the invention and vice versa.

In an advantageous development of the invention, the sealing air device is repaired by a method according to the first aspect of the invention. This is advantageous because it enables the sealing air device to be repaired in a particularly time-saving and efficient manner.

A third aspect of the invention relates to a turbomachine with at least one sealing air device according to the second aspect of the invention. The features presented in connection with the method according to the invention according to the first aspect of the invention and in connection with the sealing air device according to the invention according to the second aspect of the invention and their advantages apply accordingly to the turbo machine according to the invention according to the third aspect of the invention and vice versa.

• 1 eine schematische Darstellung einer Strömungsmaschine bei welcher ein Dichtspalt zwischen zwei Komponenten mittels eines an einem Aufnahmebereich angeordneten Dichtringes abgedichtet ist;
• 2 eine weitere schematische Darstellung der Strömungsmaschine, wobei der Dichtring aufgrund einer Beschädigung fehlt und wobei ein Vorsprung des Aufnahmebereichs beschädigt ist; und
• 3 eine weitere schematische Darstellung der Strömungsmaschine mit einer schematischen Darstellung einer Variante einer Sperrlufteinrichtung.

Further features of the invention emerge from the claims and the exemplary embodiments. The features and combinations of features mentioned above in the description, as well as the features and combinations of features mentioned below in the exemplary embodiments and / or shown alone, can be used not only in the specified combination, but also in other combinations or alone, without falling within the scope of the invention leaving. There are thus also embodiments of the invention to be regarded as encompassed and disclosed, which are not explicitly shown and explained in the exemplary embodiments, but which emerge and can be generated by separate combinations of features from the explained embodiments. Designs and combinations of features are also to be regarded as disclosed, which therefore do not have all the features of an originally formulated independent claim. It shows:

• 1 a schematic representation of a turbo machine in which a sealing gap between two components is sealed by means of a sealing ring arranged on a receiving area;
• 2 a further schematic representation of the turbomachine, wherein the sealing ring is missing due to damage and wherein a projection of the receiving area is damaged; and
• 3 a further schematic representation of the turbomachine with a schematic representation of a variant of a sealing air device.

1 shows a schematic representation of a partial area of a turbomachine 100 , in which a sealing gap 50 between two components 30th , 40 by means of a sealing ring 14th is sealed. The sealing ring 14th obstructs a blocking air flow indicated by an arrow 12th at its passage through the sealing gap 50 so that only a minor leakage of the sealing air flow 12th through the sealing gap 50 got. The first component 30th of the two components 30th , 40 includes a receiving area 32 , which is used to hold the sealing ring 14th is designed. The recording area 32 includes a groove 34 , in which the sealing ring 14th at least partially introduced and thereby in the groove 34 is recorded. The recording area 32 further comprises two protrusions 36 , 38 , between which the groove 34 extends and which to support the sealing ring 14th serve. The two protrusions 36 , 38 extend annularly in the circumferential direction U the first component 30th . The sealing ring 14th is against the second component 40 of the two components 30th , 40 pressed. In other words, the sealing ring exercises 14th a contact pressure on the second component 40 off, whereby a particularly effective sealing of the sealing gap 50 he follows.

In 2 is a state of the turbomachine 100 shown in which the sealing ring 14th is worn and as a result of a break in the sealing ring 14th can be completely absent, as can be seen here by way of example. The sealing air flow 12th can thus pass through the sealing gap almost unhindered 50 reach. Such a break in the sealing ring 14th is a symptom of wear and tear, which occurs when the turbo machine is operated for a long time 100 can come. As a result of the break, there are increased losses during operation of the turbomachine 100 .

In addition, there is also the first protrusion in the present case 36 of the two protrusions 36 , 38 damaged at least in areas, whereby a damaged zone is formed, as shown in FIG 2 is recognizable. This damaged zone corresponds to a projecting sub-area 37 of the first ledge 36 .

3 shows the turbo machine 100 partially in a repaired state, in which a sealing air device 10 the turbo machine 100 is repaired, so a method for repairing the sealing air device 10 was subjected. The air purge device 10 serves to seal the sealing gap 50 between the two components 30th , 40 compared to the sealing air flow 12th .

The first component, which is only partially shown 30th is in the present case designed as a tubular element and is used to guide an oil flow indicated by an arrow 16 . The first component 30th can also be referred to as an oil line. The second component, which is also only partially shown 40 can for example be designed as a bearing structure element and additionally or alternatively as a support structure element. This is advantageous because of the sealing gap 50 is dimensioned particularly small on such a bearing structure element or support structure element and accordingly with little leakage of the sealing air flow 12th can be sealed. In the context of the present disclosure, a bearing structure element is to be understood as a structure which is designed to absorb bearing forces such as occur, for example, in the bearing of rotating shafts. In the context of the present disclosure, a support structure element is to be understood as a structure via which components can be supported on a housing.

In the procedure for repairing the sealing air device 10 becomes at least the damaged part of the protrusion 37 of the first ledge 36 worn away. The first projection can preferably 36 can also be completely removed, as shown by 3 is recognizable. The removal can generally preferably be done by machining the first component 30th respectively.

The sealing ring is then arranged 14th and one to support the new sealing ring 14th in the axial extension direction A. the first component 30th trained support device 20th the air purge device 10 on the first component 30th . The support device 20th is doing this on an investment area 39 the air purge device 10 supported to one in the axial extension direction A. from the second ledge 38 of the two protrusions 36 , 38 away-oriented relative movement RB between the support device 20th and the second protrusion 38 to prevent. The sealing ring 14th is thereby between the support device 20th and the second protrusion 38 arranged. In addition, through the synopsis of 2 and 3 recognizable that the support device 20th in their arrangement on the first component 30th instead of the first ledge 36 , in the axial extension direction A. over a ledge area 35 extends so that the support device 20th the protrusion area 35 in the radial direction of extent R. the first component 30th overlaps. The promontory area 35 corresponds to a zone of the first component 30th , over which the removed first protrusion 36 or the projection sub-area 37 in the axial extension direction A. has extended. By removing the entire first protrusion 36 or at least the projection portion 37 can be the first component 30th at the protrusion area 35 have a surface structure which extends from the projection area 35 especially in the axial extension direction A. adjacent and thus remaining surface structures of the first component 30th can distinguish. The function of the sealing air device 10 or the support device 20th however, it is not affected.

The investment area 39 is present as the third projection of the first component 30th designed.

To simplify assembly of the support device 20th To enable this, the latter comprises two brace shells 22nd , of which in the present case, for the sake of clarity, only one support device shell 22nd is shown. The support device cups 22nd are in the radial direction of extent R. the first component 30th brought together in such a way that the support device shells 22nd the first component 30th enclose together circumferentially. When arranging the support device 20th and thus the brace shells 22nd on the first component 30th can optionally use respective elastic sealing elements 60 , 62 the air purge device 10 between the support device 20th and the first component 30th be clamped, thereby creating an effective seal between the support device 20th and the first component 30th to achieve. The elastic sealing elements 60 , 62 can be designed as respective O-rings. The support device cups 22nd can optionally by means of flexible connecting elements 64 , 66 on the first component 30th can be fixed even with very limited installation space, especially since the flexible connecting elements 64 , 66 particularly easy to an outer geometry of the support device shells 22nd can be adjusted and accordingly require little space for their assembly. The flexible connecting elements 64 , 66 can be designed as respective wires. By fixing the brace shells in place 22nd can the latter with the first component 30th tensioned and thereby the elastic sealing elements 60 , 62 between the support device 20th and the first component 30th are clamped, whereby a particularly good sealing effect can be achieved.

By arranging the supporting device 20th (and with it the brace cups 22nd ) on the first component 30th becomes a receiving gap 26th to accommodate the sealing ring 14th between the support device 20th and the second protrusion 38 educated. The intake gap 26th has at least substantially the same width in the axial direction of extent A. on how the groove 34 . The receiving gap can preferably 26th the same width in the axial extension direction A. have, like the groove 34 , as if by looking at 1 and 3 is recognizable.

The present invention allows for an exchange of the first component 30th in the event of damage in the area of the first component 30th dispensed with and thus unplanned maintenance work and delays in the use of the turbomachine 100 , which in the present case is designed as an engine, can be avoided. The present method represents a concept for repairing such damage at least with a simulation of a function of the receiving area 32 through the use of the support device 20th The support device 20th so can together with the second projection 38 the function of the recording area 32 take over so that the new sealing ring 14th in the receiving gap between the support device 20th and the second protrusion 38 can be guided and held. The support device 20th thus contributes to the sealing function of the new sealing ring 14th can be fulfilled with at least approximately the same load path, wherein the support device 20th can be used in particularly tightly limited space if the latter is the support device shells 22nd includes and is thus designed in a split design.

List of reference symbols

10

Sealing air device

12th

Sealing air flow

14th

Sealing ring

16

Oil flow

20th

Support device

22nd

Support cup

26th

Receiving gap

30th

first component

32

Recording area

34

Groove

35

Ledge area

36

first lead

37

Projection sub-area

38

second lead

39

Investment area

40

second component

50

Sealing gap

60

first sealing element

62

second sealing element

64

first flexible connecting element

66

second flexible connecting element

100

Turbo machine

A.

Direction of axial extension

R.

Radial direction of extent

RB

Relative movement

U

Circumferential direction

Claims (14)

A method for repairing a sealing air device (10) for a turbomachine (100), comprising at least the following steps: a) Provision of the sealing air device (10), which is designed to seal a sealing gap (50) between two components (30, 40) of the sealing air device (10) with respect to a sealing air flow (12), a first component (30) of the two components ( 30, 40) comprises a receiving area (32) with at least two projections (36, 38), between which extends a groove (34) for receiving a sealing ring (14) designed to seal the sealing gap (50); b) removing at least one damaged projection sub-area (37) of at least one first projection (36) of the at least two projections (36, 38); c) Arranging the sealing ring (14) and a supporting device (20) of the sealing air device (10) designed to support the sealing ring (14) in the axial extension direction (A) of the first component (30) on the first component (30), the supporting device ( 20) is supported on a contact area (39) of the sealing air device (10) in order to achieve a relative movement (RB) between the support device (20) oriented away from a second projection (38) of the two projections (36, 38) in the axial extension direction (A) and to prevent the second projection (38), and wherein the sealing ring (14) is arranged between the support device (20) and the second projection (38). Procedure according to Claim 1 , characterized in that a third projection of the first component (30) is used as the contact area (39). Procedure according to Claim 1 or 2 , characterized in that in step b) at least the damaged projection sub-area (37) is removed by machining the first component (30). Method according to one of the preceding claims, characterized in that the first projection (36) is completely removed in step b). Method according to one of the preceding claims, characterized in that the support device (20) comprises at least two support device shells (22) which are each arranged on the first component (30), whereby the support device shells (22) together circumferentially the first component (30) enclose. Procedure according to Claim 5 , characterized in that the at least two support device shells (22) are fixed to the first component (30) by means of at least one flexible connecting element (64, 66). Procedure according to Claim 6 , characterized in that a wire is used as the flexible connecting element (64, 66). Method according to one of the Claims 5 until 7th , characterized in that the at least two support device shells (22) are fixed to the first component (30) by means of at least one screw connection. Method according to one of the preceding claims, characterized in that by arranging the support device (20) on the first component (30) a receiving gap (26) for receiving the sealing ring (14) between the support device (20) and the second projection (38 ) is formed, the receiving gap (26) having at least substantially the same width in the axial direction of extent (A) as the groove (34). Method according to one of the preceding claims, characterized in that when arranging the supporting device (20) in step c) at least one elastic sealing element (60, 62) is clamped between the supporting device (20) and the first component (30). Method according to one of the preceding claims, characterized in that an O-ring is used as the at least one elastic sealing element (60, 62). Sealing air device (10) for a turbo machine (100), which is designed to seal a sealing gap (50) between two components (30, 40) of the sealing air device (10) against a blocking air flow (12), in which a first component (30) of the two components (30, 40) comprises at least one projection (38), wherein the sealing air device (10) comprises a support device (20) arranged on the first component (30) and is located between the at least one projection (36) and the support device (20 ) a receiving gap (26) extends in which a sealing ring (14) of the sealing air device (10) designed to seal the sealing gap (50) is received, the supporting device (20) for supporting the sealing ring (14) in the axial extension direction (A) of the first component (30) is formed and is supported on a contact area (39) of the sealing air device (10) in order to move in the axial direction (A) and away from the at least one projection (38) o to prevent oriented relative movement (RB) between the support device (20) and the at least one projection (38), and wherein the sealing ring (14) is arranged between the support device (20) and the at least one projection (38). Sealing air device (10) Claim 12 , characterized in that the sealing air device (10) by a method according to one of Claims 1 until 10 is repaired. Turbo machine (100) with at least one sealing air device (10) according to Claim 12 or 13th .

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