Schnittstelle zwischen Turbinendüse und -Ummantelung
Anmelder: General Electric Company 🇺🇸
Details
- Veröffentlichungs-Nr.
- EP3399152
- Aktenzeichen
- EP18169823
- Anmeldetag
- 27. April 2018
- Veröffentlichung
- 29. Januar 2020
- Erteilung
- 29. Januar 2020
- Rechtsraum
- EP
- IPC
- F01D9/04
Abstract
A turbomachine includes a compressor 12, a combustor 16, and a turbine 18. The turbine includes a nozzle 202, a shroud 206, and an axial cavity defined between the nozzle and the shroud. The nozzle includes an inner platform 208, an outer platform 210 spaced apart from the inner platform along a radial direction, and an airfoil 212 extending therebetween. The outer platform extends axially between a forward sidewall 214 and an aft sidewall 216. The nozzle also includes an aft hook 222 radially outward of the outer platform and axially forward of the aft sidewall of the outer platform. The shroud includes a forward end 226 adjacent to the aft sidewall of the outer platform. A sealing interface is positioned within the cavity, radially outward of the outer platform of the nozzle and axially forward of the aft sidewall of the outer platform of the nozzle.
Anmelder
- Firma
- General Electric Company
- Land
- 🇺🇸 USA
US-amerikanischer Technologiekonzern mit Sitz in Massachusetts. Historisch aktiv in Energieerzeugung, Luftfahrttriebwerken, Medizintechnik und Industrietechnik über verschiedene Geschäftsbereiche.
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