Turbine nozzle positioning system

Patent · Tue Jan 30 04:00:00 EST 1996

OSTI ID:187061

Norton, P F; Shaffer, J E

A nozzle guide vane assembly having a preestablished rate of thermal expansion is positioned in a gas turbine engine and being attached to conventional metallic components. The nozzle guide vane assembly includes an outer shroud having a mounting leg with an opening defined therein, a tip shoe ring having a mounting member with an opening defined therein, a nozzle support ring having a plurality of holes therein and a pin positioned in the corresponding opening in the outer shroud, opening in the tip shoe ring and the hole in the nozzle support ring. A rolling joint is provided between metallic components of the gas turbine engine and the nozzle guide vane assembly. The nozzle guide vane assembly is positioned radially about a central axis of the gas turbine engine and axially aligned with a combustor of the gas turbine engine. 9 figs.

• Research Organization: Solar Turbines Inc
• DOE Contract Number: AC02-92CE40960
• Assignee: Solar Turbines Inc., San Diego, CA (United States)
• Patent Number(s): US 5,487,642/A/
• Application Number: PAN: 8-262,179
• OSTI ID: 187061
• Country of Publication: United States
• Language: English

Related Subjects

42 ENGINEERING
ALIGNMENT
COMBUSTION CHAMBERS
DESIGN
GAS TURBINE ENGINES
NOZZLES
POSITIONING
SHAFT GUIDES
SUPPORTS