Turbine engine component with a cooling aperture
AssigneeGeneral Electric Company
InventorsHaidong Liu, Kevin R. Feldmann, Chung Han Liou, Matthew Forrester, Javier Felipe Jimenez Rincon
Life of this patent
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Abstract
A gas turbine engine including a compressor section, combustion section, and turbine section in serial flow arrangement and defining an engine core that is operationally separated into a rotor that rotates about a rotational axis and a stator that is stationary about the rotational axis. A shroud segment having a forward face and an aft face with a confronting side face extending between the forward face and the aft face. A seal slot provided in the confronting side face with a seal disposed within the seal slot. An air cooling circuit located within the shroud segment, and exhausting to the seal slot.
Claims20
A gas turbine engine comprising:
- a compressor section, combustion section, and turbine section in serial flow arrangement and defining an engine core that is operationally separated into a rotor that rotates about a rotational axis and a stator that is stationary about the rotational axis;
- a shroud segment having a forward face and an aft face with a confronting side face extending between the forward face and the aft face;
- a seal slot provided in the confronting side face;
- a seal disposed within the seal slot;
- and
- an air cooling circuit located within the shroud segment and including a cavity defined between a first side and a second side, a rear wall extending between the first side and the second side, and an outlet arranged opposite the rear wall and opening to the seal slot, the air cooling circuit exhausting from the cavity through the outlet to the seal slot to purge air within the seal slot and pressurize the seal slot.
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A component for a gas turbine engine, the component comprising:
- a body having a sealing surface with a seal slot formed into the sealing surface;
- an air cooling circuit arranged within the body, the air cooling circuit comprising:
- a cavity at least partially defined between a first side and a second side, and a rear wall extending between the first side and the second side;
- and
- an outlet exhausting from the cavity and arranged at the seal slot opposite the rear wall to purge air within the seal slot and pressurize the seal slot.
A component for a gas turbine engine, the component comprising:
- a body having a hot surface, a cold surface spaced from the hot surface, and a sealing surface;
- a cavity defined within the body and at least partially defined between a first side and a second side, a rear wall extending between the first side and the second side, and the cavity including an outlet exhausting at the sealing surface opposite the rear wall to purge air within the seal slot and pressurize the seal slot;
- and
- an impingement surface at least partially defining the cavity and extending between the first side and the second side;
- wherein the impingement surface is positioned proximate to the hot surface and spaced from the hot surface by the body.
Dependencies are inferred from the claim text.