Turbine nozzle vane suspension for gas turbine engines

US4384822A · kind A · utility

Assignee

• Motoren- und Turbinen-Union Munchen GmbH · DE

Inventors

• Ludwig Schweikl · Moosburg an der Isar, DE
• Horst Weiss · Karlsruhe, DE
• Friedrich Sippel · Stein, DE

Key dates

• Filing date: Jan 26, 1981
• Grant date: May 24, 1983
• Expiry date: Jan 26, 2001

Classification

• Technology area (CPC Y): Emerging Cross-Sectional Technologies
• CPC primary: Y02T50/60
• WIPO field: Engines, pumps, turbines
• WIPO sector: Mechanical engineering

Abstract

A turbine nozzle vane suspension arrangement of the type wherein the nozzle vanes are suspended by their outer shroud segments from the outer turbine casing and are suspended by their vane ring segments from an annular vane carrier. The vane carrier has axially spaced apart and radially-extending wall sections cooperating with root-ends projecting radially from the vane ring segments. The vane ring segments and their root-ends, and the vane carrier and its wall sections define between them an annular channel for receiving cooling air. The forward wall section of the vane carrier is axially resilient and bears resiliently against the forward vane root-end to provide a seal for the annular channel. The resilient forward wall section can be flexed axially rearwardly to permit the vane ring segments to be mounted on the vane carrier. Seals are provided between the cooperating wall sections and root-ends, or at least some of the contacting surfaces of the wall sections and root-ends are provided with wear-inhibiting and abraidable coatings.