High altitude turbine engine starting system

Patent · Tue Aug 03 00:00:00 EDT 1993

OSTI ID:6468750

Shekleton, J R

A turbine engine is described, comprising: a rotor including turbine blades and a nozzle adjacent the turbine blades, the nozzle being adapted to direct hot gases of combustion at the turbine blades to cause rotation of the rotor; an annular combustor about the rotor and having an outlet to the nozzle, the annular combustor having spaced inner and outer walls interconnected by a generally radially extending walls, the annular combustor also including a combustion annulus defined by the inner, outer and radially extending walls upstream of the outlet; a housing substantially surrounding the annular combustor in spaced relation to the inner, outer and radially extending walls thereof, the housing defining an air flow path including a compressed air inlet in communication with a source of compressed air at one end thereof, the air flow path extending from the compressed air inlet at least part way about the annular combustor; means for injecting fuel from a source into the combustion annulus, the fuel injecting means including control means integrally associated therewith for injecting fuel at an optimum flow rate and pressure, the control means being directly responsive to instantaneous operating conditions; and means for bleeding compressed air from the air flow path in a substantially uniform manner, the compressed air bleeding means including valve means integrally associated therewith for bleeding compressed air at a variable rate from an intermediate point along the air flow path, the valve means being directly responsive to instantaneous operating conditions.

• Assignee: Sundstrand Corp., Rockford, IL (United States)
• Patent Number(s): US 5231822; A
• Application Number: PPN: US 7-699514
• OSTI ID: 6468750
• Resource Relation: Patent File Date: 14 May 1991
• Country of Publication: United States
• Language: English

Related Subjects

33 ADVANCED PROPULSION SYSTEMS
GAS TURBINE ENGINES
DESIGN
ANNULAR SPACE
COMBUSTORS
COMPRESSED AIR
FUEL INJECTION SYSTEMS
NOZZLES
OPERATION
ROTORS
TURBINE BLADES
AIR
COMPRESSED GASES
CONFIGURATION
ENGINES
FLUIDS
FUEL SYSTEMS
GASES
HEAT ENGINES
INTERNAL COMBUSTION ENGINES
SPACE
330103* - Internal Combustion Engines- Turbine