High pressure fluid ejector for engine starting turbines

Claim 1

IN A FLUID PRESSURE OPERATED TURBINE STARTER FOR AN AIRCRAFT ENGINE OF THE TYPE ENCLOSED IN A CASING, THE STARTER BEING SECURED TO THE ENGINE AND HAVING AN INLET FOR FLUID UNDER PRESSURE AND AN EXHAUST OUTLET LEADING TO THE EXTERIOR OF THE ENGINE CASING, AN AUXILIARY FLUID PRESSURE SOURCE COMPRISING: A SECOND INLET MEANS MOUNTED ON THE STARTER AND COMMUNICATING AT ONE END WITH THE FIRSTMENTIONED INLET, THE OTHER END TERMINATING IN A COUPLING SECTION ADJACENT AN OPENING IN THE ENGINE CASING; A UNIT ADAPTED TO BE ATTACHED TO, SUPPORTED BY, AND DETACHED FROM SAID SECOND INLET MEANS, SAID UNIT HAVING A CARTRIDGE RECEIVING BREECH; AN EJECTOR MEANS FORMED FOR ATTACHMENT TO AND REMOVAL FROM SAID BREECH, SAID EJECTOR HAVING A CONVERGING-DIVERGING NOZZLE COMMUNICATING WITH SAID BREECH AND DIVERGING MIXING TUBE WITH AN OUTWARDLY FLARED INLET END SURROUNDING SAID NOZZLE AND OPENING TO THE ATMOSPHERE; AND A COMPLEMENTAL COUPLING SECTION AT THE OUTLET END OF SAID MIXING TUBE FOR CONNECTION WITH THE COUPLING SECTION ON SAID SECOND INLET MEANS.