Jacking assembly for rotor

Abstract

A jacking assembly for a rotor of a turbine includes an arc-shaped saddle which extends around and supports a lower portion of a rotor. A lifting beam extends over the rotor transversely to an axial direction of the rotor. The lifting beam is axially aligned with the arc-shaped saddle. Two connectors are disposed on respective lateral sides of the rotor, each connector extending between and being coupled to the lifting beam and the arc-shaped saddle such that the saddle is configured to lift the rotor vertically when the lifting beam is displaced vertically.

Claims

1. A rotor jacking system for a turbine or generator, comprising: a rotor rotatably disposed in a turbine or generator; and a jacking assembly comprising: an arc-shaped saddle configured to extend around and support a lower portion of the rotor without removing the rotor from the turbine or generator, the saddle having two blind holes formed therein; a lifting beam configured to extend over the rotor transversely to an axial direction of the rotor, the lifting beam being axially aligned with the arc-shaped saddle; and two connectors disposed on respective lateral sides of the rotor, each connector extending between and being attached respectively to the lifting beam and the arc-shaped saddle such that the arc-shaped saddle is positioned spaced-apart from the lifting beam, the connectors being received, respectively, in the two blind holes without passing through a rear side of the saddle, wherein one or both of the two connectors is configured to facilitate rotating the saddle around the rotor, while the rotor is disposed in the turbine or generator, until the saddle is positioned beneath the lower portion of the rotor, and wherein the saddle is configured to lift the rotor vertically when the lifting beam is displaced vertically.

2. The rotor jacking system of claim 1, further comprising two lifting devices disposed on respective lateral sides of the rotor, each lifting device configured to support a portion of the lifting beam.

3. The rotor jacking system of claim 2, wherein each lifting device is configured to move vertically so as to displace vertically the lifting beam.

4. The rotor jacking system of claim 3, wherein the two lifting devices are mechanical jacks.

5. The rotor jacking system of claim 1, wherein the arc-shaped saddle has a semicircular shape.

6. The rotor jacking system of claim 1, wherein the two connectors are threaded rods.

7. The rotor jacking system of claim 6, wherein the two connectors are coupled to the lifting beam by retaining members.

8. The rotor jacking system of claim 7, wherein the retaining members are nuts received on the threaded rods.

9. The rotor jacking system of claim 1, wherein the lifting beam in configured to be displaced vertically so as to lift the rotor a distance of 0.008 to 0.0225 inches.

10. The rotor jacking system of claim 9, wherein the lifting beam in configured to be displaced vertically so as to lift the rotor a distance of 0.01 to 0.02 inches.

11. The rotor jacking system of claim 1, further comprising an arc-shaped retaining member connected to the saddle and configured to extend around an upper portion of the rotor so as to hold the saddle beneath the lower portion of the rotor.

12. The rotor jacking system of claim 1, wherein each connector has a first end directly attached to the arc-shaped saddle.

13. A gas turbine system, comprising: a compressor section; a turbine; a thrust cage cavity; and a rotor jacking system, comprising: a rotor rotatably disposed in the turbine; and a jacking assembly comprising: an arc-shaped saddle configured to extend around and support a lower portion of the rotor without removing the rotor from the turbine, the saddle having two blind holes formed therein; a lifting beam configured to extend over the rotor transversely to an axial direction of the rotor, the lifting beam being axially aligned with the arc-shaped saddle; and two connectors disposed on respective lateral sides of the rotor, each connector extending between and being attached respectively to the lifting beam and the arc-shaped saddle such that the arc-shaped saddle is positioned spaced-apart from the lifting beam, the connectors being received, respectively, in the two blind holes without passing through a rear side of the saddle, wherein one or both of the two connectors is configured to facilitate rotating the saddle around the rotor, while the rotor is disposed in the turbine, until the saddle is positioned beneath the lower portion of the rotor, and wherein the saddle is configured to lift the rotor vertically when the lifting beam is displaced vertically, wherein the rotor is coupled to the compressor section and the turbine, and wherein the saddle is positioned in the thrust cage cavity.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) The accompanying drawings facilitate an understanding of the various examples of this technology. In such drawings:

(2) FIG. 1 is a cross-section of a gas turbine according to an example of the disclosed technology;

(3) FIG. 2 is a perspective view showing a portion of a forward end of a gas turbine with a jacking assembly according to an example of the disclosed technology;

(4) FIG. 3 is a partial perspective view of a saddle being lowed around a forward end portion of the rotor according to an example of the disclosed technology;

(5) FIG. 4 is a perspective view of a jacking assembly according to an example of the disclosed technology;

(6) FIG. 5 is a perspective view of another jacking assembly according to an example of the disclosed technology;

(7) FIG. 6 is a perspective view showing a portion of an aft end of a gas turbine according to an example of the disclosed technology;

(8) FIG. 7 is a perspective view of a saddle according to an example of the disclosed technology;

(9) FIG. 8 is another perspective view of the saddle of FIG. 7;

(10) FIG. 9 is a side view of the saddle of FIG. 7;

(11) FIG. 10 is a perspective view of the saddle of FIG. 7 being installed on the aft end of the rotor according to an example of the disclosed technology;

(12) FIG. 11 is another perspective view of the saddle of FIG. 7 being installed on the aft end of the rotor according to an example of the disclosed technology; and

(13) FIG. 12 is another perspective view of the saddle of FIG. 7 being installed on the aft end of the rotor according to an example of the disclosed technology.

DETAILED DESCRIPTION OF THE ILLUSTRATED EMBODIMENTS

(14) Referring to FIG. 1, a cross-section of a gas turbine 10 is shown. The illustrated gas turbine 10 includes a combustor section 12 and a turbine 14. As those skilled in the art will recognize, the gas turbine includes other conventional components that are not described here.

(15) The turbine 14 is coupled to the compressor 12 via a rotor or shaft 20. Also shown in FIG. 1 is a forward end jacking assembly 30 for jacking up a forward end 22 of rotor 20. An aft end jacking assembly 40 is shown at an aft end 24 of rotor 20 for jacking up this portion of the rotor.

(16) As shown in FIGS. 1, 2 and 4, the jacking assembly 30 includes a saddle 32. The saddle 32 has an arc shape and is configured to extend around and support a lower portion of the rotor 20. In the illustrated example, the saddle 32 has a semicircular shape. A pair of connectors 34 are configured to be coupled to opposing ends of the saddle. In the illustrated example, the connectors 34 are threaded rods which are screwed into threaded holes in the upper end faces of the saddle.

(17) The connectors 34 extend through respective through-holes in lifting beam 36, as shown in FIGS. 2 and 4. Locking members (e.g., nuts 38) may be positioned on connectors 34 above and beneath the lifting beam 36 to fix the location of the lifting beam relative to the connectors 34. The lifting beam 36 extends over the rotor 20 transversely to an axial direction of the rotor and is axially aligned with the saddle 32. Lifting beam 36 has an elongate rectangular shape, but those skilled in the art will recognize that the lifting beam may have other shapes (e.g., square).

(18) A lifting device (e.g., mechanical jack 50) is positioned beneath the lifting beam 36 on each side of the rotor. The jacks 50 are configured to support a portion of the lifting beam 36. The jacks 50 are also configured to jack up lifting beam 36 which in turn causes the saddle 32 to lift the rotor. The jacks 50 use positive stop such that there is essentially no creep down over time. That is, due to their mechanical construction, the jacks can be continually loaded supporting the rotor for long periods of time (e.g., several weeks) with no creep down. The forward 22 and aft 24 ends of rotor 20 may each weight around 50,000 lbs.

(19) As can be seen in FIG. 3, the thrust bearing is removed from the thrust cage cavity 53, in order to provide room to install the saddle 32. The saddle 32 is rotated around rotor 20 until it is positioned beneath the lower portion of the rotor. The upper half 55 of the journal bearing (bearing #1) at the forward end 22 of the rotor may be removed prior to lifting the rotor.

(20) The jacking assembly 30 is configured to lift the rotor a distance of 0.008 to 0.0225 inches (or 0.02032 to 0.5715 mm), preferably 0.01 to 0.02 inches (or 0.254 to 0.508 mm). As such, rotor 20 is not removed from the turbine. Instead, rotor 20 is raised such a small distance that the rotor remains in the turbine while lifted just enough to unload the weight of the rotor from the journal bearing.

(21) Jacking assembly 30 is configured to hold the rotor in the lifted position while the lower half of bearing #1 is removed, inspected or replaced. While the rotor is lifted, a major inspection may be performed on the turbine. For example, steam cleaning tools and borescopes may be used to clean and inspect the lower half stator vanes while the rotor is lifted but still in place in the turbine.

(22) Unlike the jacking position at the forward end 22 of rotor 20, the jacking position at the aft end 24 is near an end portion of the rotor, as can be seen in FIG. 6. Additionally, a small clearance space d1 exists between the end of the rotor 20 and surrounding support structure. Also, a large space exists below the rotor 20 at the jacking position, such that a semicircular saddle may simply fall away from the rotor.

(23) As such, a saddle 42 having an arc-shaped retaining member 45 attached thereto is utilized for jacking up the aft end 24 of rotor 20, as shown in FIGS. 5, 7 and 8. Saddle 42 is similar to saddle 32. The retaining member 45 is connected to the saddle 42. In the illustrated example, the retaining member 45 has a semicircular shape and has opposing ends connected respectively to opposite ends of the saddle.

(24) Similar to forward end jacking assembly 30, aft end jacking assembly 40 includes connectors 44 (e.g., threaded rods), a lifting beam 46, retaining members (e.g., nuts 48) and lifting devices (e.g., mechanical jacks 50), as shown in FIG. 5.

(25) As shown in FIG. 9, saddle 42 has a width d2. An aft edge of the retaining member 45 is positioned a distance d3 from a forward edge of the saddle. As can be seen in FIG. 9, d3 is smaller than d2. Referring to FIGS. 6 and 9, it is noted that d2 is larger than d1 while d3 is smaller than d1.

(26) As such, the saddle 42 is positioned on the rotor with the retaining member 45 is located downwardly so as to fit into the clearance space d1, as shown in FIGS. 10 and 11. Once positioned on the rotor, the saddle 42 and retaining member 45 are rotated to position the saddle beneath a lower portion of the rotor. The retaining member 45 is supported on an upper portion of the rotor and functions to prevent the saddle from falling away from the lower portion of the rotor. In this manner, the saddle may be positioned at the correct axial position for lifting the rotor.

(27) Similar to the jacking assembly 30, jacking assembly 40 is configured to lift the rotor a distance of 0.008 to 0.0225 inches, preferably 0.01 to 0.02 inches. Referring to FIG. 6, while the rotor is lifted, the lower half 64 of the journal bearing (bearing #2) at the aft end of the rotor may be removed, inspected or replaced. As mentioned above, a major inspection may also be performed on the turbine.

(28) While the invention has been described in connection with what is presently considered to be the most practical and preferred examples, it is to be understood that the invention is not to be limited to the disclosed examples, but on the contrary, is intended to cover various modifications and equivalent arrangements included within the spirit and scope of the appended claims.