Rear outer discharge nozzle

Abstract

A rear outer discharge nozzle for a gas turbine engine, the rear outer discharge nozzle forming a loop around an axis and comprising: a first part; a second part wrapped around the first part; and a radial slit, having first and second side walls; wherein the first part is shaped to provide the first side wall of the radial slit, and the second part is shaped to provide the second side wall of the radial slit; and wherein the second part comprises a break, splitting the second part in the axial part.

1 . A rear outer discharge nozzle for a gas turbine engine, the rear outer discharge nozzle forming a loop around an axis and comprising:
 a first part;   a second part wrapped around the first part; and   a radial slit, having first and second side walls;   wherein the first part is shaped to provide the first side wall of the radial slit, and the second part is shaped to provide the second side wall of the radial slit; and   wherein the second part comprises a break, splitting the second part along the axial direction.   
     
     
         2 . A rear outer discharge nozzle according to  claim 1 , wherein the second part comprises fastening points either side of the break. 
     
     
         3 . A rear outer discharge nozzle according to  claim 2 , wherein the fastening points are attached to the second part. 
     
     
         4 . A rear outer discharge nozzle according to  claim 2 , wherein the fastening points are integrally formed with the second part. 
     
     
         5 . A rear outer discharge nozzle according to  claim 1 , wherein the second part is fastened to the first part. 
     
     
         6 . A rear outer discharge nozzle according to  claim 1 , wherein the first and second part engage, to inhibit angular rotation of the second part with respect to the first part around the axis. 
     
     
         7 . A rear outer discharge nozzle according to  claim 6 , wherein the first part comprises a projection, and the second part comprises a slot that fits around the projection. 
     
     
         8 . A rear outer discharge nozzle according to  claim 6 , wherein the first part comprises a slot, and the second part comprises a projection that fits within the slot. 
     
     
         9 . A rear outer discharge nozzle according to  claim 6 , wherein the first part comprises a projection that fits within the break. 
     
     
         10 . A rear outer discharge nozzle according to  claim 1 , further comprising an anti-rotation part configured to inhibit angular rotation of the second part with respect to the first part around the axis. 
     
     
         11 . A rear outer discharge nozzle according to  claim 10 , wherein the first part comprises an orifice and the second part comprises another orifice, and anti-rotation part is a fastening element attached to the second part and passing through the orifice in the first part and the orifice in the second part. 
     
     
         12 . A rear outer discharge nozzle according to  claim 10 , wherein the first part comprises a first slot, the second part comprises a second slot aligned with the first slot, and wherein the anti-rotation part is a locking plate positioned within the first and second slot to thereby lock the relative positions of the first and second parts. 
     
     
         13 . A gas turbine engine comprising a rear outer discharge nozzle according to  claim 1 . 
     
     
         14 . A method of assembling a gas turbine engine, the method comprising:
 positioning a first part of a rear outer discharge nozzle so as to form a first side wall of a radial slit around radial rails of high pressure nozzle guide vanes in the gas turbine engine;   positioning a second part of a rear outer discharge nozzle to wrap around the first part and to form a second side wall of the radial slit; and   fastening the first part to the second part, to thereby attach the rear outer discharge nozzle around the high pressure nozzle guide vanes.   
     
     
         15 . A method of assembling a gas turbine engine according to  claim 14 , wherein the second part comprises two or more pieces. 
     
     
         16 . A gas turbine engine combustion arrangement comprising a combustion chamber, a rear outer discharge nozzle and an array of turbine nozzle guide vanes,
 the combustion chamber comprising an outer combustion liner, the outer combustion liner of the annular combustion chamber having a downstream end,   the array of turbine nozzle guide vanes having outer platforms, the outer platforms of the turbine nozzle guide vanes having radial rails, the array of turbine nozzle guide vanes being located downstream of the combustion chamber,   the rear outer discharge nozzle being located between the downstream end of the outer combustion liner of the combustion chamber and the array of turbine nozzle guide vanes,
 the rear outer discharge nozzle having an annular axially extending slot, the downstream end of the outer combustor liner of the combustion chamber locating in the annular axially extending slot in the rear outer discharge nozzle, 
   the rear outer discharge nozzle having an annular radially extending slot, the annular radially extending slot having first and second side walls, the radial rails on the outer platforms of the turbine nozzle guide vanes locating in the annular radially extending slot in the rear outer discharge nozzle,   the rear outer discharge nozzle forming a loop around an axis and comprising:
 a first part having the annular axially extending slot; 
 a second part wrapped around the first part; and 
 the first part is shaped to provide the first side wall of the annular radially extending slot, and the second part is shaped to provide the second side wall of the annular radially extending slot; 
 wherein the second part comprises a break, splitting the second part along an axial direction such that the second part is not a complete loop, the second part has two ends separated by the break; and 
   the second part is fastened to the first part.   
     
     
         17 . A gas turbine engine combustion arrangement as claimed in  claim 16 , wherein the two ends of the second part comprise fastening points and the fastening points of the second part are removably fastened together. 
     
     
         18 . A gas turbine engine combustion arrangement as claimed in  claim 16 , wherein the second part comprises two or more breaks splitting the second part along an axial direction into two or more pieces.