Method for the manufacture of a circular revolution thermomechanical part including a titanium-based load-bearing substrate lined with steel or superalloy, a turbomachine compressor housing which is resistant to titanium fire obtained according to this method

Abstract

A method for manufacture of a compressor housing which is resistant to a titanium fire (burning titanium). An explosion cladding of a circular blank made of steel, or steel alloy, or superalloy which is incombustible in the presence of a titanium fire is accomplished on a circular blank made from titanium or titanium alloy.

1 - 11 . (canceled) 
     
     
         12 . A method for manufacture of a circular revolution thermomechanical part including a load-bearing substrate made from titanium or titanium alloy lined with a steel or superalloy, the method comprising:
 a) production of a preform made from titanium or titanium alloy having a general circular shape as close as possible to a shape and external dimensions of the part to be manufactured;   b) production of a preform made from steel, or steel alloy, or superalloy incombustible in presence of burning titanium, having a general circular shape of diameter(s) less than the circular blank made from titanium or titanium alloy and as close as possible to a shape and internal dimensions of the part to be manufactured;   c) machining, using the internal dimensions of the part to be manufactured, the inner surface of the blank made from steel, or steel alloy, or superalloy;   d) assembly with fitting of the blank made from steel, or steel alloy, or superalloy in the blank made from titanium or titanium alloy; and   e) explosion cladding of the blank made from steel, or steel alloy, or superalloy on the blank made from titanium or titanium alloy under process conditions such that undulations created at an interface have no fragile phases in a course of thermomechanical cycles to which the part is subsequently subjected.   
     
     
         13 . A method according to  claim 12 , wherein the production a) includes beta or alpha-beta forging of a titanium alloy. 
     
     
         14 . A method according to  claim 12 , wherein the production b) includes pre-rolling or rolling of a plate or by drawn rolled welded techniques using steel, or steel alloy, or superalloy. 
     
     
         15 . A housing comprising:
 at least a part constituting a structure holding rows of stator blades; and   an inner wall demarcating an outer contour of a compressor airstream in which are mounted rows of rotating rotor blades individually sandwiched with the rows of stator blades; and   means of thermal protection against burning titanium, including at least along one part of its length, as a load-bearing structure, a part of titanium or titanium alloy on to which is clad a layer of steel, steel alloy, or superalloy, which is incombustible in presence of burning titanium, and wherein the layer of steel, steel alloy, or superalloy constitutes the means of thermal protection and the inner wall demarcating the outer contour of the compressor airstream.   
     
     
         16 . A housing according to  claim 15 , wherein the steel or steel alloy is chosen from among Inconel® 909 or Inconel® 783. 
     
     
         17 . A housing according to  claim 15 , wherein the titanium alloy is chosen from among Ti 6 4, Ti 6242, or Ti 6246. 
     
     
         18 . A housing according to  claim 15 , wherein a length of the clad part corresponds only to a part of the annular length of the housing. 
     
     
         19 . A housing according to  claim 15 , wherein on an inner diameter of the clad part or downstream from the length on to which it is attached, a wear material configured to define the outer contour of the airstream is attached on to a part made of titanium or titanium alloy. 
     
     
         20 . A high-pressure axial compressor comprising, as a stator, a housing according to  claim 15 . 
     
     
         21 . A high-pressure compressor according to  claim 20 , wherein the length of the housing constitutes only an upstream part of the compressor, and wherein an inner wall demarcating an outer contour of the downstream airstream is made from titanium or titanium alloy. 
     
     
         22 . An aircraft engine comprising a compressor according to  claim 20 .