Turbomachine modification apparatus and method

Patent metadata

Field	Value
Publication number	US-11053796-B2
Application number	US-201916279355-A
Country	US
Kind code	B2
Filing date	Feb 19, 2019
Priority date	Feb 20, 2018
Publication date	Jul 6, 2021
Grant date	Jul 6, 2021

Abstract

A turbomachine modification apparatus includes a machining device, and a machining device mount attached to the machining device. The machining device mount is configured to radially and axially adjust a position of the machining device. A blade mount is configured to be attached to one or more turbomachine blades. The blade mount is attached to the machining device mount.

First claim

What is claimed is:

1. A method for modifying a static seal or shroud in a turbomachine, the method comprising:
attaching a blade mount to one or more turbomachine blades;
attaching a machining device mount to the blade mount;
attaching a machining device to the machining device mount, the machining device including a machining bit;
positioning the machining bit in a desired location with respect to the static seal or shroud;
activating the machining device;
controlling a rotor of the turbomachine so that the rotor rotates at a desired speed; and
wherein rotation of the rotor moves the machining device in an arcuate and circumferential path along the static seal or shroud thereby machining the static seal or shroud; the blade mount further including:
an aft plate and a forward plate, the aft plate configured to be placed on an aft side of the turbomachine blades and the forward plate configured to be placed on a forward side of the turbomachine blades; and
each of the aft plate and the forward plate includes grooves generally conforming to a profile of the turbomachine blades.

2. The method of claim 1 , the controlling step further including controlling the rotor to rotate at a speed of about 2 to about 5 revolutions per hour (RPH).

3. The method of claim 2 , wherein a drill is attached to a turning gear motor of the rotor to obtain the rotor speed of about 2 RPH to about 5 RPH.

4. The method of claim 1 , wherein the positioning, activating, controlling and machining the static seal or shroud steps are performed multiple times until a desired level of machining is obtained.

5. The method of claim 1 , the positioning step further including positioning the machining bit in a gap between adjacent seal or shroud sections.

6. The method of claim 1 , the machining device mount configured to radially and axially adjust a position of the machining device.

7. The method of claim 6 , wherein the positioning step includes adjusting the position of the machining device in radial and axial directions with respect to the turbomachine.

8. The method of claim 1 , wherein the aft plate and the forward plate are substantially parallel to each other when installed on the one or more turbomachine blades.

9. The method of claim 1 , wherein the machining the static seal or shroud step is performed on a static honeycomb seal.

10. A method for modifying a static honeycomb seal or shroud in a turbomachine, the method comprising:
attaching a blade mount to one or more turbomachine blades;
attaching a machining device mount to the blade mount;
attaching a machining device to the machining device mount, the machining device including a machining bit, the machining bit configured for machining the static honeycomb seal or shroud;
positioning the machining bit in a desired location with respect to the static honeycomb seal or shroud;
activating the machining device;
controlling a rotor of the turbomachine so that the rotor rotates at a desired speed; and
wherein rotation of the rotor moves the machining device in an arcuate and circumferential path along the static honeycomb seal or shroud thereby machining the static honeycomb seal or shroud, the blade mount further including:
an aft plate and a forward plate, the aft plate configured to be placed on an aft side of the turbomachine blades and the forward plate configured to be placed on a forward side of the turbomachine blades;
each of the aft plate and the forward plate comprising grooves generally conforming to a profile of the turbomachine blades; and
wherein the aft plate and the forward plate are substantially parallel to each other when installed on the turbomachine blades.

11. The method of claim 10 , the controlling step further including:
controlling the rotor to rotate at a speed of about 2 to about 5 revolutions per hour (RPH).

12. The method of claim 11 , wherein a drill is attached to a turning gear motor of the rotor to obtain the rotor speed of about 2 RPH to about 5 RPH.

13. The method of claim 10 , wherein the positioning, activating, controlling and machining the static honeycomb seal or shroud steps are performed multiple times until a desired level of machining is obtained.

14. The method of claim 8 , the positioning step further including positioning the machining bit in a gap between adjacent static honeycomb seal or shroud sections.

15. The method of claim 8 , the machining device mount configured to radially and axially adjust a position of the machining device.

16. The method of claim 8 , wherein the positioning step includes adjusting the position of the machining device in radial and axial directions with respect to the turbomachine.

Assignees

• Gen Electric

Inventors

• Dzieciol Piotr Krzysztof
• Kobek Piotr Edward
• Perkowski Szymon
• Dolecki Mateusz

Classifications

• F05D2230/80

  Repairing, retrofitting or upgrading methods · CPC title

• F01D25/285 Primary

  Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such structures · CPC title

• F01D11/02

  by non-contact sealings, e.g. of labyrinth type (for sealing space between rotor blade tips and stator F01D11/08) · CPC title

• F01D5/005 Primary

  Repairing methods or devices · CPC title

• B23C1/027

  with working-spindle movable in a vertical direction · CPC title