Seal system for a gas turbine

Patent metadata

Field	Value
Publication number	US-10012101-B2
Application number	US-201414574846-A
Country	US
Kind code	B2
Filing date	Dec 18, 2014
Priority date	Dec 20, 2013
Publication date	Jul 3, 2018
Grant date	Jul 3, 2018

Abstract

The invention pertains to a seal system for a passage between a turbine stator and a turbine rotor, including: a first arm extending radially outwards from the turbine rotor and toward the first seal arranged on the stator, and terminating short of the first seal thereby creating a first gap between the first seal and the first arm. The seal system further includes a second seal arranged on the turbine stator, and a second arm extending axially from the turbine rotor towards the second seal base, and terminating short of the second seal thereby creating a second gap between the second seal and the second arm. The invention further refers to a gas turbine including such a seal system.

First claim

The invention claimed is:

1. A seal system for a passage between a turbine stator and a turbine rotor of a turbine, the seal system comprising:
a first seal base facing radially inwards from the turbine stator,
a first seal attached to the first seal base and extending radially inwards from the first seal base,
a first arm extending radially outwards from the turbine rotor and toward the first seal, and terminating short of the first seal thereby creating a first gap between the first seal and the first arm,
a second seal base facing in an axial direction from the turbine stator, a second seal attached to the second seal base and extending axially from the second seal base towards the turbine rotor,
a second arm extending axially from the turbine rotor towards the second seal base, and terminating short of the second seal thereby creating a second gap between the second seal and the second arm; and
a locking plate attached to a row of rotating blades from which at least one of the first arm and the second arm extend.

2. The seal system according to claim 1 , further comprising an outer cavity delimited by the first arm the second arm and surfaces of the turbine stator facing the first arm and second arm.

3. The seal system according to claim 2 , wherein the turbine stator comprises two components facing the outer cavity with a seal or slot interposed, the seal or slot having a predetermined leakage rate for purging the outer cavity.

4. The seal system according to claim 1 , wherein the first seal and/or the second seal is made of a honeycomb material or is made of an abradable material.

5. The seal system according to claim 1 , wherein the second arm extends further in the axial direction towards the turbine stator than the first arm.

6. The seal system according to claim 1 , wherein the first seal base is on a side of a platform of a turbine vane facing away from a hot gas path of the turbine.

7. A gas turbine comprising:
a compressor, a combustion chamber, a turbine stator, a turbine rotor, and a seal system including:
a first seal base facing inwards from the turbine stator,
a first seal attached to the first seal base and extending radially inwards from the first seal base,
a first arm extending radially outwards from the turbine rotor and toward the first seal, and terminating short of the first seal thereby creating a first gap between the first seal and the first arm,
a second seal base facing in an axial direction from the turbine stator, a second seal attached to the second seal base and extending axially from the second seal base towards the turbine rotor,
a second arm extending axially from the turbine rotor towards the second seal base, and terminating short of the second seal thereby creating a second gap between the second seal and the second arm; and
a locking plate attached to a row of rotating blades from which at least one of the first arm and the second arm extend.

8. The gas turbine according to claim 7 , further comprising an annular cavity extending radially inwards from the second arm between turbine stator and a turbine rotor, and in that it comprises a purge air supply into the annular cavity.

9. The gas turbine according to claim 7 , wherein the turbine stator and the turbine rotor are designed to have a difference in thermal expansion such that the first gap provided between the first arm and the first seal closes during operation relative to the first gap at cold condition of the gas turbine, and/or that the turbine stator and the turbine rotor are designed to have a difference in thermal expansion such that the second gap provided between the second arm and the second seal closes during operation in cold conditions.

10. The gas turbine according to claim 7 , wherein the turbine stator and the turbine rotor are designed to have a difference in thermal expansion such that the second gap closes to a minimum gap or to a point where the second arm extends into the second seal due to a faster thermal expansion of the turbine stator relative to the thermal expansion of the turbine rotor during transient warm up and opens to a gap wider than the minimum gap during steady state operation of the gas turbine.

11. The gas turbine according to claim 7 , wherein the turbine stator and the turbine rotor are designed to have a difference in thermal expansion such that the first gap opens to a maximum gap due to a faster thermal expansion of the turbine stator relative to the thermal expansion of the turbine rotor during transient warm up and closes to a gap smaller than the maximum gap during steady state operation of the gas turbine.

12. The gas turbine according to claim 7 , wherein the turbine stator and the turbine rotor are designed to have a difference in thermal expansion such that the first gap closes to a minimum gap or to a point where the first arm extends into the first seal due to a faster thermal contraction of the turbine stator relative to the thermal contraction of the turbine rotor during transient cool down, and/or in that the turbine stator and the turbine rotor are designed to have a difference in thermal expansion such that the second gap opens to a maximum gap due to a faster thermal contraction of the turbine stator relative to the thermal contraction of the turbine rotor during transient cool down of the gas turbine.

Assignees

• Ansaldo Energia Ip Uk Ltd

Inventors

• Simon-Delgado Carlos
• Didion Christoph
• Widmer Marc
• Schaefer Martin
• Filkorn Guenter

Classifications

• F01D11/122

  with erodable or abradable material (blades having cutting or grinding tips F01D5/20) · CPC title

• F01D11/127

  with a deformable or crushable structure, e.g. honeycomb · CPC title

• F05D2250/283

  honeycomb · CPC title

• F01D11/18 Primary

  using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion · CPC title

• F01D11/001

  for sealing space between stator blade and rotor · CPC title