Patent ID: 6843515
Filing Date: 2005-01-18
Classification: F16L

Abstract:
1. An aircraft comprising a cooling system, said cooling system comprising fluid flow pipes including pipe sections ( 1 , 2 ) having pipe ends ( 10 , 11 ) arranged to face each other, a spacing (S) between said pipe ends ( 10 , 11 ) facing each other, a shrunk hose member ( 12 ) having hose ends ( 8 , 9 ) encircling and overlapping said pipe ends facing each other thereby forming a pipe junction with a shrink fit providing a fluid and pressure tight seal between said hose ends and said pipe ends, said shrunk hose member having between its hose ends a hose portion bridging said spacing (S), said hose portion having, after shrinking, a flexibility which in combination with said spacing (S) between said pipe ends permits a tolerance in the positioning of said pipe ends relative to each other when said pipe sections are being installed in said aircraft, said flexibility along said spacing (S) taking up vibrations during operation of said aircraft, and wherein said shrunk hose member is made of a material having the following characteristics in combination, a shrink temperature within the range of 125° C. to 135° C., a temperature resistance within the range of −40° C. to +95° C., an operational pressure resistance within the range of −30 mbar to +30 mbar, a testing pressure resistance up to and +45 mbar, a burst pressure of at least +95 mbar, and is non-toxic.