Pipe connections for aircraft gas turbine engines

Claim 1

IN AN AXIAL FLOW COMPRESSOR INCORPORATED IN A GAS TURBINE ENGINE FOR THE PROPULSION OF AIRCRAFT, SAID COMPRESSOR COMPRISING HOLLOW ELEMENTS AT THE INTAKE END THEREOF WHICH ARE SUBJECT TO ICING, AND CONDUIT MEANS CONDUCTING PRESSURIZED, HEATED ANTIICING AIR TO SAID HOLLOW ELEMENTS FROM AN AFTER PORTION OF THE COMPRESSOR, A SLIP CONNECTION INTERPOSED IN SAID CONDUIT MEANS, SAID CONNECTION COMPRISING A PAIR OF TUBULAR MEMBERS RESPECTIVELY CONNECTABLE AT OPPOSITE ENDS TO SAID CONDUIT MEANS AND TELESCOPE TOGETHER, THE OUTER TUBULAR MEMBER HAVING A SMOOTH BORE THERETHROUGH, THE INNER TUBULAR MEMBER HAVING A PAIR OF SPACED CIRCUMFERENTIAL RIBS DEFINING AT THEIR INNER ENDS A RETAINER GROOVE, THE INWARDMOST TELESCOPED RIB HAVING A CIRCUMFERENTIAL GROOVE, A PAIR OF SPLIT SEALING RINGS DISPOSED IN SAID GROOVE AND SEALINGLY ENGAGING THE BORE OF THE OUTER TUBULAR MEMBER, THE SPLIT ENDS OF SAID RINGS BEING ANGULARLY OFFSET TO PREVENT LEAKAGE THEREPAST, SAID OUTER TUBULAR MEMBER HAVING AN ENLARGED WRENCHING PORTION INTERMEDIATE ITS LENGTH TO FACILITATE ITS ATTACHMENT TO THE CONDUIT MEANS, AND A RETAINER MEMBER INSERTABLE THROUGH SAID WRENCHING PORTION INTO SAID RETAINER GROOVE TO LIMIT RELATIVE AXIAL MOVEMENT OF THE TWO TUBULAR MEMBERS.