Aircraft cooling system with fluid and pressure-tight pipe junctions
View Patent ↗A cooling system in an aircraft has fluid flow pipe sections that are mounted to the aircraft structure. The pipe sections have pipe ends that form part of pipe junctions. The two pipe ends of a pipe junction are facing each other and are surrounded by a shrunk hose member of a shrinkable material which overlaps both pipe ends in a fluid- and pressure-tight manner.
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.
2. The aircraft of claim 1 , further comprising an adhesive between an outer surface of said pipe ends and an inner surface of said hose ends, said adhesive being pressure-, water-, and coolant-resistant.
3. A method for forming a flexible fluid end pressure-tight pipe junction between two pipe ends in an aircraft, said method comprising the following steps:
a) using a shrinkable hose member made of a material that is heat shrinkable within a temperature range of 125° C. to 135° C. and during a shrinking time within a time range of 0.5 minutes to 2.0 minutes,
b) selecting said shrinkable hose member to have an initial inner diameter that fits onto an outer diameter of said two pipe ends and retains a flexibility after a shrinking step is completed,
c) inserting said pipe ends into said shrinkable hose member to such an extent that a spacing (S) remains between said pipe ends facing each other inside said hose member, and
d) heating said shrinkable hose member to ate a temperature within said temperature range for a duration within said time range, thereby shrinking said shrinkable hose member onto said pipe junction to form a fluid- and pressure-tight pipe junction that remains flexible.