High temperature turbine engine structure

Patent · Tue Jul 20 00:00:00 EDT 1993

OSTI ID:6356203

Carruthers, W D; Boyd, G L

A hybrid ceramic/metallic gas turbine is described comprising; a housing defining an inlet, an outlet, and a flow path communicating the inlet with the outlet for conveying a flow of fluid through the housing, a rotor member journaled by the housing in the flow path, the rotor member including a compressor rotor portion rotatively inducting ambient air via the inlet and delivering this air pressurized to the flow path downstream of the compressor rotor, a combustor disposed in the flow path downstream of the compressor receiving the pressurized air along with a supply of fuel to maintain combustion providing a flow of high temperature pressurized combustion products in the flow path downstream thereof, the rotor member including a turbine rotor portion disposed in the flow path downstream of the combustor and rotatively expanding the combustion products toward ambient for flow from the turbine engine via the outlet, the turbine rotor portion providing shaft power driving the compressor rotor portion and an output shaft portion of the rotor member, a disk-like metallic housing portion journaling the rotor member to define a rotational axis therefore, and a disk-like annular ceramic turbine shroud member bounding the flow path downstream of the combustor and circumscribing the turbine rotor portion to define a running clearance therewith, the disk-like ceramic turbine shroud member having a reference axis coaxial with the rotational axis and being spaced axially from the metallic housing portion in mutually parallel concentric relation therewith and a plurality of spacers disposed between ceramic disk-like shroud member and the metallic disk-like housing portion and circumferentially spaced apart, each of the spacers having a first and second end portion having an end surface adjacent the shroud member and the housing portion respectively, the end surfaces having a cylindrical curvature extending transversely relative to the shroud member and the housing portion.

• Assignee: Allied-Signal Inc., Morris Township, NJ (United States)
• Patent Number(s): US 5228284; A
• Application Number: PPN: US 7-842870
• OSTI ID: 6356203
• Resource Relation: Patent File Date: 27 Feb 1992
• Country of Publication: United States
• Language: English

Related Subjects

33 ADVANCED PROPULSION SYSTEMS
GAS TURBINE ENGINES
DESIGN
CERAMICS
COMBUSTORS
COMPRESSORS
MECHANICAL SHAFTS
PRESSURIZATION
ROTORS
SHROUDS
TURBINE BLADES
TURBINES
COOLING SYSTEMS
ENERGY SYSTEMS
ENGINES
EQUIPMENT
HEAT ENGINES
INTERNAL COMBUSTION ENGINES
MACHINE PARTS
MACHINERY
REACTOR COMPONENTS
REACTOR COOLING SYSTEMS
SHAFTS
TURBOMACHINERY
330103* - Internal Combustion Engines- Turbine