Device for sealing turbomachines

• US 6,832,891 B2
• Filed: 10/10/2002
• Issued: 12/21/2004
• Est. Priority Date: 10/29/2001
• Status: Expired due to Fees

• Current Assignee: MAN Turbo AG (Volkswagen AG)
• Original Assignee: MAN Turbomaschinen AG (Volkswagen AG)
• Inventors: Ebbing, Hildegard, Mohr, Klaus Dieter, Aschenbruck, Emil, Kleinefeldt, Andreas
• Primary Examiner(s): Look, Edward K.
• Assistant Examiner(s): MCALEENAN, JAMES M
• Application Number:
  US10/268,422
• Publication Number:
  US 20030082050A1
• Time in Patent Office: 803 Days
• Field of Search: 415/173.7, 415/174.4, 415/174.5, 415/115, 415/116, 415/47, 416/96.R, 416/96.A, 416/97.R
• US Class Current: 415/173.7
• CPC Class Codes: F01D 11/001 for sealing space between stator blade and rotor
• CPC Class Codes: F01D 11/025 Seal clearance control; Floating assembly; Adaptation means to differential thermal dilatations

Abstract

A device for sealing between the guide vanes (1) and the rotor (17) of turbomachines, especially gas turbines has inner rings (3) suspended on the vane footing (14) of the guide vanes (1) in a thermally elastic manner with soldered honeycomb seal (4) and labyrinth tips (5) arranged on the rotor (17). First flow channels, which are connected to the cavities (21) of the cooled guide vanes (1), through which said cavities cooling air flows, are led through the vane footings (14). The first flow channels are connected to at least one of second flow channels led through the inner ring (3) to the vicinity of the honeycomb seal (4). The second flow channels open into at least one of third flow channels that are open at the rear edge of the inner ring (3) or are led to an annular groove (10) open toward the honeycomb seal (4) on the underside of the inner ring (3).

Claims

1. A device for sealing between guide vanes and a rotor of a gas turbine turbomachine, the device comprising:

a cavity within each guide vane, said cavity being blown through by cooling air, each guide vane having a footing;

an inner ring with a recess on an outer rim of said inner ring, wherein said inner ring is suspended on said vane footing in a thermally elastic manner;

an attachment connected to said footing of each said guide vanes;

a centering pin coupling, said attachment to said recess;

a honeycomb seal soldiered to said footing;

labyrinth tips arranged on the rotor and being located opposite said honeycomb seal;

a first flow channel connected to said cavity of said guide vane, said first flow channel comprising a hole passing through said vane footing of said guide vane; and

a second flow channel connected to said first flow channel, said second flow channel comprising a second hole passing through said inner ring into the vicinity of said honeycomb seal and having at least one connection leading to the outside of the inner ring.

2. A device in accordance with claim 1, further comprising an axial third flow channel including an opening affixed at rear edge of said inner ring wherein said second flow channel joins said axial third flow channel.

3. A device in accordance with claim 1, wherein said second flow channel is led to an annular groove open toward said honeycomb seal on an underside of said inner ring, said annular groove forming said at least one connection of said second flow channel leading to the outside of said inner ring.

4. A device in accordance with claim 3, further comprising:

a further flow channel connected to another annular groove open toward the honeycomb seal on the underside of said inner ring, said further flow channel being branched off from said second flow channel.

5. A device in accordance with claim 1, wherein said first flow channel comprises an inner hole led through a hollow centering pin and a hole connecting said inner hole to said cavity of said guide vane.

6. A device in accordance with claim 1, wherein said second flow channel comprises a hole led radially through said inner ring or a hole led three-dimensionally diagonally, and a third flow channel is provided as a hole led axially through said inner ring, and a fourth flow channel is provided as a hole led obliquely through said inner ring.

7. A device in accordance with claim 1, wherein said inner ring comprises two parts provided with grooves and projections on sides facing each other and said grooves and projections engage one another to form a serpentine-like further flow channel to which at least one connection leading to the outside of said inner ring is connected.

8. A device in accordance with claim 1, wherein said honeycomb seal is protected by the cooling air discharged from said honeycomb seal and/or said inner ring against the break-in of hot gas.

9. A device in accordance with claim 1, wherein the amount of the cooling air fed to the inner ring is regulated and that depending on the amount of the cooling air, the leakage flows flowing through a gap between said honeycomb seal and said labyrinth tips can flow only forward or both forward and backward.

10. A device in accordance with claim 1, wherein an amount of cooling air fed to said inner ring is regulated by a pressure of the cooling air in said guide vane, a diameter of said holes or a selected shape of an inlet and an outlet of said holes.

11. A device for sealing between guide vanes and a rotor of a gas turbine turbomachine, the device comprising:

a set of guide vanes, each said guide vane further comprising;

a cavity within said guide vane;

a footing at inner rim of said guide vane;

an attachment coupled to said footing;

a centering pin with a first distal end and a second distal end, wherein said first distal end is inserted into said attachment;

a first flow channel connected to said cavity and formed through said footing; and

a stream of cooling air flowing from said cavity through said first flow channel;

an inner ring having an outer rim with a recess and an inner rim, said inner ring suspended on said footing in a thermally elastic manner, said second distal end of said centering pin being inserted into a bottom of said recess to align said inner ring with said footing;

a honeycomb seal attached to said inner rim;

a set of labyrinth tips arranged on the rotor and being located opposite said honeycomb seal; and

a second flow channel joined to said first flow channel, said second flow channel formed through said inner ring into the vicinity of said honeycomb seal and having at least one opening affixed to outside of said inner ring.

12. A device in accordance with claim 11, further comprising an axial third flow channel including an opening affixed at rear edge of said inner ring wherein said second flow channel joins said axial third flow channel.

13. A device in accordance with claim 12, wherein said second flow channel includes an annular groove opening affixed to said honeycomb seal on the underside of said inner ring, said annular groove opening leading to outside of said inner ring.

14. A device in accordance with claim 12, further including a tertiary flow channel having a first end joined to said second flow channel and having other end joined to second annular groove opening on the underside of said inner ring toward the honeycomb seal.

15. A device in accordance with claim 12, wherein said first flow channel comprises an inner hole led through a hollow centering pin and a hole connecting said inner hole to said cavity of said guide vane.

16. A device in accordance with claim 12, wherein said second flow channel comprises a hole led radially through said inner ring or a hole led three-dimensionally diagonally, and a third flow channel is provided as a hole led axially through said inner ring, and a fourth flow channel is provided as a hole led obliquely through said inner ring.

17. A device in accordance with claim 12, wherein said inner ring comprises two parts provided with grooves and projections on sides facing each other and said grooves and projections engage one another to form a serpentine-like further flow channel to which at least one connection leading to the outside of said inner ring is connected.

18. A device in accordance with claim 12, wherein said honeycomb seal is protected by the cooling air discharged from said honeycomb seal and/or said inner ring against the break-in of hot gas.

19. A device in accordance with claim 11, wherein the amount of the cooling air fed to the inner ring is regulated and that depending on the amount of the cooling air, the leakage flows flowing through a gap between said honeycomb seal and said labyrinth tips can flow only forward or both forward and backward.

20. A device in accordance with claim 12, wherein an amount of cooling air fed to said inner ring is regulated by a pressure at the cooling air in said guide vane, a diameter of said holes or a selected shape of an inlet and an outlet of said holes.