Gas turbine with plurality of tie rods and method of assembling the same

Patent metadata

Field	Value
Publication number	US-2016146101-A1
Application number	US-201514798614-A
Country	US
Kind code	A1
Filing date	Jul 14, 2015
Priority date	Nov 21, 2014
Publication date	May 26, 2016
Grant date	—

Abstract

Disclosed herein is a gas turbine with a plurality of tie rods. The gas turbine includes a compressor section having a plurality of compressor-side rotor disks, a turbine section having a plurality of turbine-side rotor disks arranged downstream of the compressor-side rotor disks, a first tie rod penetrating central portions of the rotor disks provided in the compressor section to press the compressor-side rotor disks against each other, a plurality of second tie rods penetrating vicinities of edges of the rotor disks provided in the turbine section to press the turbine-side rotor disks against each other, and a torque transfer member coupled to the first and second tie rods so as to transfer rotational torque generated by the turbine section to the compressor section.

First claim

1 . A gas turbine comprising:
a compressor section having a plurality of compressor-side rotor disks; a turbine section having a plurality of turbine-side rotor disks arranged downstream of the compressor-side rotor disks; a first tie rod penetrating central portions of the rotor disks provided in the compressor section to press the compressor-side rotor disks against each other; a plurality of second tie rods penetrating vicinities of edges of the rotor disks provided in the turbine section to press the turbine-side rotor disks against each other; and a torque transfer member coupled to the first and second tie rods so as to transfer rotational torque generated by the turbine section to the compressor section.

2 . The gas turbine according to claim 1 , wherein the torque transfer member comprises a first end facing the compressor section, and the first end has a first through-hole through which the first tie rod passes.

3 . The gas turbine according to claim 2 , further comprising a first pressure nut fastened to one side of the first tie rod,
wherein the first pressure nut presses an inside surface of the first end toward the compressor section.

4 . The gas turbine according to claim 3 , wherein at least a portion of the first pressure nut is inserted into the first through-hole.

5 . The gas turbine according to claim 3 , wherein the torque transfer member comprises a second end facing the turbine section, and the second end has a plurality of second through-holes arranged radially such that the second tie rods pass through the second through-holes.

6 . The gas turbine according to claim 5 , further comprising a second pressure nut fastened to one side of each of the second tie rods,
wherein the second pressure nut presses an inside surface of the second end toward the turbine section.

7 . The gas turbine according to claim 6 , wherein the second end has a service hole communicating with the inside of the torque transfer member, and access to the first and second pressure nuts is realized through the service hole.

8 . The gas turbine according to claim 5 , wherein the torque transfer member has a reinforcement portion formed between the first and second ends to protrude toward a center of the torque transfer member.

9 . The gas turbine according to claim 8 , wherein the torque transfer member has an inner diameter increased toward the reinforcement portion from the first and second ends.

10 . A gas turbine comprising:
a compressor section having a plurality of compressor-side rotor disks; a turbine section having a plurality of turbine-side rotor disks arranged downstream of the compressor-side rotor disks; a first tie rod penetrating central portions of the rotor disks provided in the compressor section to press the compressor-side rotor disks against each other; a plurality of second tie rods penetrating vicinities of edges of the rotor disks provided in the turbine section to press the turbine-side rotor disks against each other; and a torque tube comprising a first end facing the compressor section and a second end facing the turbine section, the torque tube being coupled to the first and second tie rods.

11 . The gas turbine according to claim 10 , wherein a first pressure nut fastened to the first tie rod is arranged to the first end, and second pressure nuts fastened to the second tie rods are arranged to the second end.

12 . The gas turbine according to claim 11 , wherein the second pressure nuts are radially arranged on the second end, and the second end has service holes which are formed radially and inwardly of the second pressure nuts and communicate with the inside of the torque tube.

13 . The gas turbine according to claim 12 , wherein each of the service holes has a diameter increased toward the first end.

14 . The gas turbine according to claim 10 , wherein the torque transfer member has a reinforcement portion formed between the first and second ends to protrude toward a center of the torque transfer member.

15 . The gas turbine according to claim 14 , wherein the reinforcement portion has a larger inner diameter than an outer diameter of the first pressure nut.

16 . The gas turbine according to claim 14 , wherein the torque transfer member has an inner diameter increased toward the reinforcement portion from the first and second ends.

17 . A method of assembling a turbine, comprising:
inserting a plurality of first rotor disks to a first tie rod in a longitudinal direction thereof; inserting a torque tube from one side end of the first tie rod; fixing an end of the first tie rod to the torque tube in a state in which the first rotor disks are not rotated relative to the torque tube; fixing a plurality of second tie rods to a portion of the torque tube; inserting a plurality of second rotor disks to the plurality of second tie rods in a longitudinal direction thereof; and fixing an end of each of the plurality of second tie rods to one of the rotor disks in a state in which the second rotor disks are not rotated relative to the torque tube.

18 . The method according to claim 17 , wherein the first tie rod is inserted to penetrate central portions of the first rotor disks.

19 . The method according to claim 17 , wherein the second tie rods are spaced radially and outwardly from centers of the second rotor disks to penetrate the second rotor disks.

20 . The method according to claim 17 , wherein the first rotor disks are arranged in a compressor section.

Assignees

• Doosan Heavy Ind Constr Co Ltd

Inventors

• Lee Sang Eon

Classifications

• F02C3/04 Primary

  having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) · CPC title

• F01D5/066 Primary

  Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps · CPC title

• F16C3/02

  Shafts; Axles · CPC title

• F16C2360/23

  Gas turbine engines · CPC title

• F05D2230/644

  for adjusting the position or the alignment, e.g. wedges or eccenters · CPC title