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    • 150. 发明专利
    • DE69011731D1
    • 1994-09-29
    • DE69011731
    • 1990-03-31
    • VICKERS INC
    • HANSEN LOWELL D
    • F02M37/08F02C7/22F02C7/236F02M37/18F04B23/12F04D1/04F04D7/02F04D9/06F04D13/12F04D29/18F04D29/42F04D29/66F04B23/14
    • A hydraulic fluid pump (10, 90) for aircraft turbine engine fuel delivery systems comprises a housing (12, 96) having a pump drive shaft (16) mounted for rotation therewithin. A centrifugal pump stage (26) includes an impeller (28) coupled to the drive shaft (16) and having a circumferential array of radially extending passages (30) with inlet ends adjacent to the shaft (16) and outlet ends at the periphery of the impeller (28). An inducer stage (34) includes a spiral inducer (36) coupled to the shaft (16) to rotate coaxially with the impeller (28) and having an outlet end adjacent to the inlet end of the impeller passages (30). An injector stage (42, 102) includes a passage (44) in the housing for feeding fluid to the inlet end of the inducer, and a circumferential array of nozzle orifices (90, 104) in the housing aligned with the injector passage and receiving fluid from a collection cavity (32) that surrounds the periphery of the impeller. The pump inlet is fed to the injector passage, with the injector nozzles (90, 104) cooperating with the passage to boost fluid pressure and flow through the passage to the inducer inlet, which in turn boosts fluid pressure and flow to the impeller (28).