WO2020112137A1

WO2020112137A1 - Method for removing a rotor member from a turboengine, and instrumentation useful to conduct the method

Info

Publication number: WO2020112137A1
Application number: PCT/US2018/063304
Authority: WO
Inventors: Michael Gerard Lynch; Piotr Hubert WOJCIECHOWSKI; John Porter; Alexander Kling
Original assignee: General Electric Company
Priority date: 2018-11-30
Filing date: 2018-11-30
Publication date: 2020-06-04

Abstract

Disclosed is a method for removing a rotor member from a turboengine (1). A rotor member (11) of the turboengine comprises a rotor body (110) equipped with running blades provided in running blade rows (112), and a trunnion (113, 114) at each axial end of the rotor body. The method comprises providing the turboengine removing a casing provided around the rotor body, installing a rotor support device (3) below the rotor body to support the rotor member (11), removing the central casing (13), providing a suspension device (5, 51) and connecting the suspension device (5, 51) to the rotor member (11) so as to suspend the rotor member, removing the rotor support device (3), and removing the rotor member (11) by a movement along an axis of the rotor member while at least essentially maintaining an inclination of the axis of the rotor member with respect to the ground.

Description

METHOD FOR REMOVING A ROTOR MEMBER FROM A TURBOENGINE, AND INSTRUMENTATION USEFUL TO CONDUCT THE METHOD

TECHNICAL FIELD

The present disclosure relates to a method for removing a rotor member from a turboengine as set forth in the claims. It further relates to instrumentation useful to conduct the method.

BACKGROUND OF THE DISCLOSURE

Maintenance of turboengines may require removal of the rotor or a rotor member. State of the art methods of rotor removal for certain turboengines require tilting the turboengine with the axis of the rotor, or the rotor member, respectively, from an operational orientation of the axis to a vertical orientation of the axis. It will be appreciated that an operational orientation of the axis commonly, at least for stationary installed turboengines, is at least essentially horizontal. It is apparent that tilting a turboengine accordingly, and performing the disassembly steps safely, requires special instrumentation, and may moreover require shipping the turboengine to an accordingly equipped service shop. The required steps add logistics expense, may extend outage times, and thus adds cost to turboengine maintenance. Moreover, the process of first tilting the turboengine with the axis of the rotor or the rotor member vertical, removing the rotor or rotor member with a vertical axis, subsequently tilting the rotor or rotor member back to a horizontal axis position to place it on rotor stands, and further the need to perform the process in a reverse order for re-assembling the turboengine, is a cumbersome and expensive task.

OUTLINE OF THE SUBJECT MATTER OF THE PRESENT DISCLOSURE

It is an objective of the present disclosure to propose a method and useful instrumentation as initially mentioned. It is a more specific objective of the present disclosure to describe a method which facilitates removal of a rotor member from a turboengine, and further to provide an instrumentation which is useful in

performing the method. In more specific aspects, the method and the

instrumentation shall allow removal of the rotor member without the need to tilt the axis of the rotor member, so that the axis of the rotor member may be maintained in an operational, or, in more specific embodiments, horizontal, orientation throughout the method.

This is achieved by the subject matter described in claim 1.

It shall be understood that the tilting action referred to, and which is to be avoided, refers to adding an inclination to the axis of the rotor member. Rotating the axis of the rotor member about an at least essentially vertical axis, that is, rotating the axis of the rotor member at least essentially leveled to the ground, shall not be understood as a tilting movement and is possible throughout the herein described method. Further effects and advantages of the disclosed subject matter, whether explicitly mentioned or not, will become apparent in view of the disclosure provided below.

It is noted that within the framework of the present disclosure the use of the indefinite article“a” or“an” does in no way stipulate a singularity nor does it exclude the presence of a multitude of the named member or feature. It is thus to be read in the sense of“at least one” or“one or a multitude of”.

Accordingly, disclosed is a method for removing a rotor member from a

turboengine, wherein the turboengine comprises a rotor, the rotor comprising a compressor rotor member and a turbine rotor member detachably attached to each other, wherein a rotor member comprises a rotor body, the rotor body being equipped with running blades provided in running blade rows, and a trunnion at each axial end of the rotor body. It is understood that the running blade rows are arranged in an axial distance from each other, so as to allow guide vane rows to be placed between each pair of adjacent running blade rows. A first one of the trunnions is a bearing trunnion supported by one of a front bearing and an aft bearing, or compressor-sided and turbine-sided bearings, and the other one of said trunnions is a central trunnion extending into a central casing when the turboengine is assembled. In more specific instances, the rotor member is a compressor rotor member and the bearing trunnion is received within a

compressor bellmouth and supported by a front bearing provided in the bellmouth when the turboengine is assembled. The central trunnion then may be referred to as an aft trunnion, whereas the bearing trunnion may be referred to as a front trunnion. The method further comprises providing the turboengine with a rotor axis in an operational orientation. As noted above, the operational orientation may in particular be at least essentially horizontal. The rotor members are detached from each other, and a casing provided around the rotor body is removed.

Subsequently, a rotor support device is installed below the rotor body to support the rotor member, the central casing is removed, a suspension device is provided, and the suspension device is connected to the rotor member so as to suspend the rotor member. This may comprise transferring the weight load of the rotor member to the suspension device. After the rotor member is safely carried by the suspension device, the method further comprises removing the rotor support device and removing the rotor member by a movement along an axis of the rotor member and in a direction towards the central trunnion, while at least essentially maintaining an inclination of the axis of the rotor member with respect to the ground. Removing the rotor support may be understood as at least“disengaging” the rotor support device and the rotor member so as to enable axial movement of the rotor member without interfering with the rotor support device. It is understood that the steps of the method herein disclosed and claimed are not restricted to be performed in the order of appearance in the claims or description, unless it is explicitly so stated. The skilled person will understand that certain method steps may be performed in different order, to the extent this is technically feasible, without deviating from the teaching of the present disclosure. The skilled person will readily appreciate which steps need to be performed compulsorily in the stated order, and which ones may be conducted in a different order.

In more specific embodiments, installing the rotor support device comprises installing at least two rotor support plates, each between two adjacent rows of running blades, and installing the support plates in a functional support

relationship with a shaft of the rotor body. A functional support relationship will be readily understood as the support plates being placed so as to be in contact with the shaft of the rotor body and being able to support the weight of the rotor member. Installing the rotor support device may in further aspects comprise placing the rotor support device below the rotor body and jacking the support plates to get into contact and functional support relationship with the shaft of the rotor body. In particular, in order to enable the functional support relationship between the support plates and the shaft of the rotor body, the method may further comprise at least one of providing the rotor support device with a distance between at least two support plates such that the at least two support plates fit into axial spaces provided between the rows of running blades, and/or adjusting a distance between at least two support plates such that the at least two support plates fit into axial spaces provided between adjacent rows of running blades.

In further aspects, the method may comprise installing a central casing support device to support a lower part of the central casing before removing the central casing.

In still further aspects, a supplementary support device may be installed to support the central trunnion after removal of the central casing, and/or a brace may be installed across a bearing housing in which the bearing trunnion is supported and axially distal from a face of the bearing trunnion, thus providing an axial stop for the rotor member in an axial direction towards the bearing trunnion. These measures add safety to the support of the rotor member before the weight load of the rotor member is safely transferred to the suspension device and while transferring the weight load of the rotor member to the suspension device, and still further when initiating an axial movement of the rotor member to remove the rotor member.

The method may comprise placing a provisional support member below the bearing trunnion. To this extent, the rotor member may have been jacked so as to move the bearing trunnion free of the bearing in which it is operationally

supported. The provisional support member may in particular be made from a material which is softer than the bearing trunnion, and which may in particular comprise at least one of wood and/or plastics. Thus, damages to the surface of the bearing trunnion while moving the rotor member may be avoided. It is understood that the provisional bearing member may in particular exhibit the shape of a section of an annulus, and may further in particular extend circumferentially 180° or less.

In further aspects of the present disclosure, a rotor support device for use in connection with a method as outlined above is disclosed. The rotor support device comprises a support base and exhibits a height and a length. The skilled person will readily understand that it is intended to install the rotor support device with the length oriented at least essentially parallel to an axis of the rotor member, and the height spanning a distance from the ground on which the rotor support device is placed to the rotor member. At least two height adjustable support tables are provided distant from each other along the length orientation of the rotor support device and adjustable in the height orientation of the rotor support device, wherein at least one support plate is provided on top of at least two support tables, with the support plate with its planar surface being oriented across, in more particular embodiments at least essentially normal to, the length orientation. The thickness of at least two support plates is dimensioned such that the support plates fit into a space between two adjacent rows of running blades. In particular, a distance between at least two support plates may be such that the support plates fit into axial spaces provided between the rows of running blades, and/or may be accordingly adjustable. It is understood in this respect that the support device may be intended for use with a specific rotor member, with known and fixed distances between the rows of running blades, so that these dimensions are well-defined. An upper boundary of at least one support plate, and in particular of each support plate, may exhibit a concave edge section which is adapted and configured to receive the shaft of the rotor body.

In certain embodiments of the rotor support device, a height adjustment appliance is provided between each support table and the support base. The height adjustment appliance may comprise a hydraulic jacking device so as to facilitate adjusting the height of the upper edges of the support plates and installing the support plates in a functional support relationship with the rotor member, and in particular with the shaft of the rotor body. The height adjustment appliance may in other aspects comprise at least one bolt-nut arrangement adapted and configured to lock the height of the support table so as to enhance safety and reliability of the support of the rotor member.

It is understood that the features and embodiments disclosed above may be combined with each other. It will further be appreciated that further embodiments are conceivable within the scope of the present disclosure and the claimed subject matter which are obvious and apparent to the skilled person.

BRIEF DESCRIPTION OF THE DRAWINGS The subject matter of the present disclosure is now to be explained in more detail by means of selected exemplary embodiments shown in the accompanying drawings. The figures show

Figures 1 - 6 various stages of removing a rotor member;

Fig. 7 a detailed view of an exemplary aft rotor support arrangement; and

Fig 8 a detailed view of an exemplary front rotor support arrangement.

It is understood that the drawings are highly schematic, and details not required for instruction purposes may have been omitted for the ease of understanding and depiction. It is further understood that the drawings show only selected, illustrative embodiments, and embodiments not shown may still be well within the scope of the herein disclosed and/or claimed subject matter. EXEMPLARY MODES OF CARRYING OUT THE TEACHING OF THE PRESENT DISCLOSURE

Figures 1 through 6 illustrate an exemplary embodiment of the herein described method. Figure 1 shows a compressor section of a turboengine 1 . The compressor housing has been removed. The turbine section has been removed. A turbine rotor member has been detached from compressor rotor member 1 1 . Compressor rotor member 1 1 comprises rotor body 1 10 and trunnions 1 13 and 1 14 extending at axial ends of compressor rotor member 11 . Front trunnion 1 13 extends into compressor bellmouth 12 and is supported by a front bearing provided inside bellmouth 12. Central trunnion 114 extends into central casing 13. The skilled person will readily understand that in an assembled turboengine the turbine section of the turboengine may be provided beyond central casing 13 when seen from the compressor section, and the turbine rotor may be attached to central trunnion 1 14. Rotor body 1 10 comprises a shaft 1 1 1 , and rows of running blades 1 12, only some of which are denoted by reference numerals, are provided on shaft 1 1 1 and axially spaced from each other. The axis of the rotor, or rotor member 11 , respectively, is provided in an operational orientation. This operational orientation, in the shown exemplary embodiment, and in most practical stationary turboengine installations, is at least essentially horizontal. In other embodiments, the rotor axis may have an operational orientation relative to the ground on which it is installed. The operational orientation is to be understood as an orientation in which the rotor axis is provided when the turboengine is installed for operation. To further proceed with disassembling the turboengine and removing rotor member 1 1 , a rotor support device 3 is installed below the rotor body to support the rotor member. Generally, rotor support plates are installed between adjacent rows 1 12 of running blades. This will be outlined in more detail in connection with figures 7 and 8. The support plates are, as will also become more apparent in connection with figures 7 and 8 and the description thereto, height adjustably attached to a support base 31. Further, a central casing support device 4 is attached to a front side of central casing 13. Central casing support device 4 may also be height-adjustable and may also be provided with a jacking capability. In that the support plates are in a functional support relationship with the shaft 1 1 1 of rotor body 1 10, rotor member 1 1 is supported by rotor support device 3. Functional support relationship between the support device and rotor may be achieved in jacking the support plates. In jacking rotor member 11 through rotor support device 3, the front bearing within bellmouth 12 is relieved. In order to additionally safeguard the temporary support of the rotor member, a front rotor brace 21 and an additional provisional front support member 22 are installed. Provisional support member 22 may for instance be a semi-annular element. Provisional support member 22 may in particular be made from a relatively soft material, like for instance, while not limited to, wood or plastics. Due to supporting bearing trunnion 1 13 on a soft provisional support member, and clearing bearing trunnion 1 13 from the front bearing, damaging the surface of bearing trunnion 1 13 or the front bearing when removing rotor member 1 1 from compressor bellmouth 12 is effectively avoided. Suspension device, crane hook, 5 is provided to take over the weight load of central casing 13. After the weight of central casing 13 is transferred to suspension device 5, central casing support device 4 may be removed.

In a next step, illustrated in figure 2, central casing 13 is suspended by crane hook 5 and is removed in an aft direction of the turboengine. As illustrated in figure 3, after the central casing has been removed, a supplementary support device 6 is installed to support central trunnion 1 14. The contacting surface of supplementary support device 6 with central trunnion 1 14 may be provided by a contacting member 61 made from a relatively soft material. Just like provisional front support member 22, contacting member 61 may for instance, while not limited to, be made from wood or plastics. The top of contacting member 61 may in particular be shaped as a concave wedge so as to safely receive central trunnion 114.

Subsequently, as shown in figure 4, suspension device, crane hook, 5 is supplemented by suspension beam 51 . Suspension beam 51 is arranged to extend at least essentially parallel to an axis of rotor member 1 1 , and is connected to the rotor member by cables. Subsequently, the weight load of rotor member 1 1 is transferred to suspension beam 51 and crane hook 5. When rotor member 1 1 is carried by suspension device 51 and 5, rotor support device 3 is removed, as shown in figure 5. Also, supplementary support device 6 may be removed. Rotor brace 21 and provisional front support member 22 may subsequently also be removed, and the suspended rotor member 11 is removed in moving it in an aft direction of the turboengine, so that finally bearing trunnion 1 13 floats out of compressor bellmouth 12. The suspended rotor member 1 1 may freely be moved to a suitable location. It is noted that an inclination of the axis of the rotor member is maintained during the entire illustrated removal process.

Figure 7 depicts the rear rotor support arrangement indicated at detail VII in figure 1 in an enlarged view. A support table 32 is height-adjustably connected to support base 31 . Two support plates 33 are provided upright and at least essentially perpendicular to the axis of the rotor member on top of support table 32. The skilled person will appreciate that a top boundary of each support plate 33 is shaped concavely so as to safely receive the shaft 1 1 1 of the rotor body. Support plates 33 are installed between adjacent rows of running blades 1 12. A hydraulic jacking device 34 is provided between support base 31 and support table 32.

Hydraulic jacking device 34 provides for the height-adjustability of support table 32. When installing the rotor support device, support table 32 with support plates

33 are lifted using the jacking device, and the top boundary of support plates 33 is brought into contact with shaft 1 1 1. In further lifting support table 32 with support plates 33 provided on top using jacking device 34, the rotor support device and shaft 11 1 are brought in a functional load bearing relationship so that the rotor member is borne by the rotor support device. Further, the rotor member may be sufficiently jacked so as to clear the trunnions from respective bearings. In addition to jacking device 34, bolt-nut arrangements 35 are provided between support base 31 and support table 32. While adjusting the height of support table 32 and support plates 33, the nuts are provided on the bolts so as to allow support table 32 to float along the bolts and move relative to support base 31 . After finalizing height adjustment, the nuts may be tightened to secure the position of support table 32 and relieve hydraulic jacking device 34. It is understood that hydraulic jacking device 34 and bolt-nut arrangements 35 jointly constitute a height adjustment appliance between the support table and the support base. Figure 8 is a detailed view of the front rotor support arrangement indicated at detail VIII in figure 1. The elements shown in figure 8 essentially fulfill the same function as those shown in figure 7. A detailed description of the embodiment shown in figure 8 is thus omitted, as the skilled person will readily appreciate the

comprehensive disclosure of figure 8 in view of the explanations given in connection with figure 7.

While the subject matter of the disclosure has been explained by means of exemplary embodiments, it is understood that these are in no way intended to limit the scope of the claimed invention. It will be appreciated that the claims cover embodiments not explicitly shown or disclosed herein, and embodiments deviating from those disclosed in the exemplary modes of carrying out the teaching of the present disclosure will still be covered by the claims.

Claims

1. A method for removing a rotor member from a turboengine (1 ), wherein the turboengine comprises a rotor, the rotor comprising a compressor rotor member (1 1 ) and a turbine rotor member detachably attached to each other, wherein a rotor member (1 1 ) comprises a rotor body (1 10), the rotor body being equipped with running blades provided in running blade rows (1 12) and a trunnion (1 13, 1 14) at each axial end of the rotor body, wherein a first one of said trunnions is a bearing trunnion (1 13) supported by one of a front bearing and an aft bearing and the other one of said trunnions is a central trunnion (1 14) extending into a central casing (13), the method comprising providing the turboengine with a rotor axis in an operational orientation, detaching the rotor members from each other, and removing a casing provided around the rotor body,

characterized in installing a rotor support device (3) below the rotor body to support the rotor member (1 1 ), removing the central casing (13), providing a suspension device (5, 51 ) and connecting the suspension device (5, 51 ) to the rotor member (1 1 ) so as to suspend the rotor member, removing the rotor support device (3), and removing the rotor member (1 1 ) by a movement along an axis of the rotor member and in a direction towards the central trunnion (1 14) while at least essentially maintaining an inclination of the axis of the rotor member with respect to the ground.

2. The method according to the preceding claim, characterized in that

installing the rotor support device (3) comprises installing at least two rotor support plates (33), each between two adjacent rows (1 12) of running blades, and installing the support plates in a functional support relationship with a shaft (1 11 ) of the rotor body (110).

3. The method according to the preceding claim, characterized in that installing the rotor support device (3) comprises placing the rotor support device below the rotor body (1 10) and jacking the support plates (33) to get into contact with the shaft (1 11 ) of the rotor body.

4. The method according to any of the two preceding claims, characterized in that installing the rotor support device (3) comprises at least one of providing the rotor support device with a distance between at least two support plates (33) such that the at least two support plates fit into axial spaces provided between the rows of running blades (1 12) and/or adjusting a distance between at least two support plates (33) such that the at least two support plates fit into axial spaces provided between the rows of running blades.

5. The method according to any of the preceding claims, the method

comprising installing a central casing support device (4) to support a lower part of the central casing (13) before removing the central casing.

6. The method according to any of the preceding claims, characterized in installing a supplementary support device (6) to support the central trunnion (1 14) after removal of the central casing.

7. The method according to any of the preceding claims, characterized in comprising installing a brace (21 ) across a bearing housing in which the bearing trunnion (1 13) is supported and axially distal from a face of the bearing trunnion, thus providing an axial stop for the rotor member in an axial direction towards the bearing trunnion.

8. The method according to any of the preceding claims, characterized in placing a provisional support member (22) below the bearing trunnion.

9. The method according to the preceding claim, characterized in providing the provisional bearing member (22) made from a material which is softer than the bearing trunnion, wherein the material of the provisional bearing member comprises in particular at least one of wood and/or plastics, and wherein further in particular the provisional bearing member exhibits the shape of a section of an annulus.

10. The method according to any of the preceding claims, characterized in that the rotor member (1 1 ) is a compressor rotor member and the bearing trunnion (1 13) is received within a compressor bellmouth (12).

1 1.A rotor support device (3) for use in connection with a method as claimed in any of the preceding claims, the rotor support device (3) comprising a support base (31 ) and having a height and a length, characterized in that at least two height adjustable support tables (32) are provided distant from each other along the length orientation of the rotor support device and adjustable in the height orientation of the rotor support device, wherein at least one support plate (33) is provided on top of at least two support tables (32), and wherein the support plate with its planar surface being oriented across the length orientation.

12. The rotor support device according to the preceding claim, characterized in that at least one support plate (33) at an upper boundary exhibits a concave edge section which is in particular adapted and configured to receive the shaft of the rotor body.

13. The rotor support device according to any of the preceding claims claiming a rotor support device, characterized in that a height adjustment appliance (34, 35) is provided between each support table and the support base.

14. The rotor support device according to the preceding claim, characterized in that the height adjustment appliance comprises a hydraulic jacking device (34).

15. The rotor support device according to any of the two preceding claims, characterized in that the height adjustment appliance comprises at least one bolt-nut arrangement (35) adapted and configured to lock the height of the support table.