초록 ▼

A booster-compressor for a high flow coefficient turboprop aircraft engine increases engine thrust by supercharging the air into the inlet of the gas generating core engine. The flow of supercharged air from the booster-compressor is split between the core engine and the ambient to allow for the use

A booster-compressor for a high flow coefficient turboprop aircraft engine increases engine thrust by supercharging the air into the inlet of the gas generating core engine. The flow of supercharged air from the booster-compressor is split between the core engine and the ambient to allow for the use of standard size rotor blades and stator blades and to provide supplemental thrust. The rotor blades are designed as impulse rotors and the stator vanes are arranged in an axially converging annular flowpath in order to limit to a minimum any increase in the static pressure of the supercharged air.

대표청구항 ▼

A booster-compressor for supercharging air into a core engine of a turboprop aircraft engine comprising: a row of rotor blades comprising a row of sub-sonic impulse rotors, said row of impulse rotors causing the static pressure of said air at an inlet of said row of impulse rotors to be substantiall

A booster-compressor for supercharging air into a core engine of a turboprop aircraft engine comprising: a row of rotor blades comprising a row of sub-sonic impulse rotors, said row of impulse rotors causing the static pressure of said air at an inlet of said row of impulse rotors to be substantially equal to the static pressure of said air at an outlet of said row of impulse rotors throughout the operating range of said turboprop aircraft engine: a row of stator vanes; and a shroud surrounding said impulse rotors and said stator vanes, wherein said shroud defines in part an axially-extending flowpath for directing said air into said core engine; wherein said flowpath defines an axially-converging flowpath along said stator vanes which causes the static pressure of said air at an inlet of said row of stator vanes to be substantially equal to the static pressure of said air at an exit of said row of stator vanes throughout the operating range of said turboprop aircraft engine; wherein said flowpath maintains a constant cross sectional area along said rotor blades; wherein each of said impulse rotors includes an inlet angle and an exit angle, said inlet angle being equal to said exit angle.