Turbine vane assembly with integrally cast cooling fluid nozzle

Patent · Tue Jun 08 04:00:00 EDT 1993

OSTI ID:6466107

Rup, Jr, J J; Nikkanen, J P

Described is a gas turbine engine disposed about a longitudinal axis and including an axially extending flow path, a turbine section, and means to conduct cooling fluid into the turbine section, the turbine section including a rotor assembly disposed circumferentially about the axis, sealing means disposed axially downstream of the rotor assembly, the rotor assembly and sealing means adapted to rotate about the axis in an operational condition, and a turbine vane assembly disposed axially downstream of the rotor assembly and radially outward of the sealing means, wherein an annular seal cavity is defined in part by the separation between the rotor assembly, the turbine vane assembly and the scaling means, the turbine vane assembly including a plurality of vanes, and a sealing shroud adapted to engage the sealing means to block the passage of fluid from the cavity, wherein each vane has a pitch angle y with [gamma][ge] [gamma][sub 1] wherein [gamma][sub 1] is the most open pitch angle, each vane including an airfoil portion, a platform, and an integrally cast nozzle, the airfoil portion being hollow and in fluid communication with the means to conduct cooling fluid, the nozzle including wall means having a flow surface facing the cavity, and a smooth, continuous flow passage in fluid communication with the airfoil portion and adapted to direct cooling fluid into the cavity, the wall means extending circumferentially between adjacent wall means and extending radially inward from the platform, each wall means having a trailing edge and a leading edge, the leading edge adapted to circumferentially align with the trailing edge of an adjacent wall means with [gamma] = [gamma][sub 1], and the leading edge adapted to form a step down relative to the direction of flow within the cavity with [gamma] > [gamma][sub 1].

• Assignee: United Technologies Corp., Hartford, CT (United States)
• Patent Number(s): US 5217348; A
• Application Number: PPN: US 7-949968
• OSTI ID: 6466107
• Country of Publication: United States
• Language: English

Related Subjects

33 ADVANCED PROPULSION SYSTEMS
330103* -- Internal Combustion Engines-- Turbine
COOLING SYSTEMS
ENERGY SYSTEMS
ENGINES
FLUIDS
GAS TURBINE ENGINES
HEAT ENGINES
INTERNAL COMBUSTION ENGINES
NOZZLES
ROTORS
SEALS
VANES
WORKING FLUIDS