Disc axis adjusting mechanism in gas turbine

Patent metadata

Field	Value
Publication number	US-9567873-B2
Application number	US-201314376035-A
Country	US
Kind code	B2
Filing date	Feb 8, 2013
Priority date	Feb 10, 2012
Publication date	Feb 14, 2017
Grant date	Feb 14, 2017

Abstract

In a disc axis adjusting mechanism in a gas turbine, the gas turbine has an exhaust gas diffuser provided between a casing wall and a bearing case which are connected to a downstream side of a turbine, a plurality of struts provided at intervals in a circumferential direction, and strut covers coupling an outer diffuser and an inner diffuser of the exhaust gas diffuser so as to cover the struts, and the mechanism comprises: a plurality of air introduction holes formed in the casing wall so as to allow the interior and exterior of the wall to communicate with each other; a sensor unit configured to detect a parameter corresponding to the thermal elongation of each of the struts; and a flow rate adjustor configured to adjust the flow rate of air flowing through each of the air introduction holes based on a detection value detected by the sensor unit.

First claim

The invention claimed is:

1. A disc axis adjusting mechanism in a gas turbine, the gas turbine having an exhaust gas diffuser having an outer diffuser and an inner diffuser provided between a casing wall and a bearing case which are connected to a downstream side of the turbine, a plurality of struts that couple the casing wall and the bearing case through the exhaust gas diffuser and are provided at intervals in a circumferential direction, and strut covers that couple the outer diffuser and the inner diffuser so as to cover the struts, the mechanism comprising:
a plurality of air introduction holes formed in the casing wall so as to correspond to each of the struts, and allow the interior and exterior of the wall to communicate with each other;
a first sensor unit configured to detect a parameter corresponding to the thermal elongation of each of the struts; and
a flow rate adjustor configured to adjust the flow rate of air flowing through each of the air introduction holes on the basis of a detection value detected by the first sensor unit.

2. The disc axis adjusting mechanism in a gas turbine according to claim 1 ,
wherein the first sensor unit is a temperature sensor that detects the temperature of the strut.

3. The disc axis adjusting mechanism in a gas turbine according to claim 2 ,
wherein the temperature sensor is a thermocouple, and
a plurality of the temperature sensors are provided along a length direction of the strut.

4. The disc axis adjusting mechanism in a gas turbine according to claim 1 ,
wherein the first sensor unit is a laser displacement gauge that is provided outside the casing wall, and causes a laser beam to pass through a region inside the strut cover having the strut interposed therein to measure the amount of displacement up to an outer peripheral portion of the bearing case.

5. The disc axis adjusting mechanism in a gas turbine according to claim 1 ,
wherein a partition plate is provided to demarcate a space between the strut cover and an inner peripheral surface of the casing wall in the circumferential direction, and
one strut is arranged within a region demarcated by the partition plate.

6. The disc axis adjusting mechanism in a gas turbine according to claim 1 ,
wherein a displacement sensor is provided in the casing wall to measure the displacement of the casing wall, and
air is blown against an outer peripheral surface of the casing wall on the basis of the displacement of the casing wall detected by the displacement sensor.

7. The disc axis adjusting mechanism in a gas turbine according to claim 2 ,
wherein the first sensor unit is a laser displacement gauge that is provided outside the casing wall, and causes a laser beam to pass through a region inside the strut cover having the strut interposed therein to measure the amount of displacement up to an outer peripheral portion of the bearing case.

8. The disc axis adjusting mechanism in a gas turbine according to claim 3 ,
wherein the first sensor unit is a laser displacement gauge that is provided outside the casing wall, and causes a laser beam to pass through a region inside the strut cover having the strut interposed therein to measure the amount of displacement up to an outer peripheral portion of the bearing case.

9. The disc axis adjusting mechanism in a gas turbine according to claim 2 ,
wherein a partition plate is provided to demarcate a space between the strut cover and an inner peripheral surface of the casing wall in the circumferential direction, and
one strut is arranged within a region demarcated by the partition plate.

10. The disc axis adjusting mechanism in a gas turbine according to claim 3 ,
wherein a partition plate is provided to demarcate a space between the strut cover and an inner peripheral surface of the casing wall in the circumferential direction, and
one strut is arranged within a region demarcated by the partition plate.

11. The disc axis adjusting mechanism in a gas turbine according to claim 4 ,
wherein a partition plate is provided to demarcate a space between the strut cover and an inner peripheral surface of the casing wall in the circumferential direction, and
one strut is arranged within a region demarcated by the partition plate.

12. The disc axis adjusting mechanism in a gas turbine according to claim 2 ,
wherein a displacement sensor is provided in the casing wall to measure the displacement of the casing wall, and
air is blown against an outer peripheral surface of the casing wall on the basis of the displacement of the casing wall detected by the displacement sensor.

13. The disc axis adjusting mechanism in a gas turbine according to claim 3 ,
wherein a displacement sensor is provided in the casing wall to measure the displacement of the casing wall, and
air is blown against an outer peripheral surface of the casing wall on the basis of the displacement of the casing wall detected by the displacement sensor.

14. A disc axis adjusting mechanism in a gas turbine, the gas turbine having an exhaust gas diffuser having an outer diffuser and an inner diffuser provided between a casing wall and a bearing case which are connected to a downstream side of the turbine, a plurality of struts that couple the casing wall and the bearing case through the exhaust gas diffuser and are provided at intervals in a circumferential direction, and strut covers that couple the outer diffuser and the inner diffuser so as to cover the struts, the mechanism comprising:
a plurality of air introduction holes formed in the casing wall so as to correspond to each of the struts, and allow the interior and exterior of the wall to communicate with each other;
a second sensor unit configured to detect a clearance between a turbine blade and a turbine casing in the turbine; and
a flow rate adjustor configured to adjust the flow rate of air flowing through each of the air introduction holes.

15. The disc axis adjusting mechanism in a gas turbine according to claim 14 ,
wherein the second sensor units are provided in a plurality of stages along a turbine axial direction.

16. The disc axis adjusting mechanism in a gas turbine according to claim 14 ,
wherein the strut is provided with a temperature sensor that detects the temperature of the strut.

17. The disc axis adjusting mechanism in a gas turbine according to claim 14 ,
wherein a displacement sensor is provided in the casing wall to measure the displacement of the casing wall, and
air is blown against an outer peripheral surface of the casing wall on the basis of the displacement of the casing wall detected by the displacement sensor.

18. The disc axis adjusting mechanism in a gas turbine according to claim 15 ,
wherein the strut is provided with a temperature sensor that detects the temperature of the strut.

19. The disc axis adjusting mechanism in a gas turbine according to claim 15 ,
wherein a displacement sensor is provided in the casing wall to measure the displacement of the casing wall, and
air is blown against an outer peripheral surface of the casing wall on the basis of the displacement of the casing wall detected by the displacement sensor.

20. The disc axis adjusting mechanism in a gas turbine according to claim 16 ,
wherein a displacement sensor is provided in the casing wall to measure the displacement of the casing wall, and

air is blown against an outer peripheral surface of the casing wall on the basis of the displacement of the casing wall detected by the displacement sensor.

Assignees

• Mitsubishi Heavy Ind Ltd

Inventors

• Ueda Motoharu
• Katou Eigo
• Ito Eisaku

Classifications

• F01D25/305 Primary

  with fluid, e.g. liquid injection · CPC title

• F05D2270/804

  Optical devices · CPC title

• F01D21/04

  responsive to undesired position of rotor relative to stator {or to breaking-off of a part of the rotor}, e.g. indicating such position · CPC title

• F01D17/02

  Arrangement of sensing elements · CPC title

• F01D9/065

  Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids (see also F01D25/16, F01D25/24 and F01D25/26) · CPC title