Assembly having an end-face cover

Abstract

An assembly having an end-face cover of a case of a turbomachine, in particular for a turbomachine having a canned design, wherein the assembly has at least the cover and an additional case. The cover has a first opening all the way through, wherein the additional case is attached to the cover, wherein the first opening leads into an interior of the additional case, wherein the additional case has a closable second opening, wherein the additional case is defined by walls, wherein at least one pipe connection of shaft feed-through is provided on the walls of the additional case.

1 .- 4 . (canceled) 
     
     
         5 . An arrangement having an end-face cover (COV) of a casing (CAS) of a turbomachine (TM), wherein the arrangement comprises:
 at least the cover (COV) and an additional casing (CAS 2 ),   wherein the cover (COV) is provided with a first continuous opening (OP 1 ),   wherein the additional casing (CAS 2 ) is attached to the cover (COV),   wherein the first opening (OP 1 ) leads into an interior of the additional casing (CAS 2 ), wherein the additional casing (CAS 2 ) is defined by walls (W), wherein at least one pipe connection or a shaft bushing is/are provided on the walls (W) of the additional casing (CAS 2 ),   wherein the walls (W) constitute a shell part (CW) and an end face (FFW),   wherein the end face (FFW) extends substantially parallel to a plane of the cover surface (COP),   wherein the shell part (CW) extends substantially perpendicularly in relation to the plane (COP),   wherein the first opening (OP 1 ) is realized in such a manner that at least visual accessibility to a radial bearing for carrying a rotor (R) of the turbomachine (TM) is afforded through the first opening (OP 1 ),   wherein the additional casing (CAS 2 ) has a closable second opening (OP 2 ),   wherein the shell part (CW) of the additional casing (CAS 2 ) is divided along a joint (TF) extending perpendicularly in relation to the plane (COP),   wherein the covering part (CWC) of the shell part (CW) that is at the top, relative to gravity (g), when the cover (COV) is in an operating position is releasable and removable from the rest of the shell part (CW), in the joint (TF).   
     
     
         6 . The arrangement as claimed in  claim 5 , further comprising:
 an oil pump (OLP), wherein the oil pump (OLP) is attached to the additional casing (CAS 2 ) from the outside, to the end face (FFW).   
     
     
         7 . The arrangement as claimed in  claim 6 ,
 wherein the cover (COV) has a gear unit (GEA), which is kinematically connected to the oil pump (OLP), and which has at least one gear ratio and at least one coupling (CUP) for coupling the gear unit (GEA) to a drive shaft, through the first opening (OP 1 ).   
     
     
         8 . The arrangement as claimed in  claim 5 ,
 wherein the end face (FFW), in the flat extent parallel to the plane (COP), is delimited by the covering part (CWC) in such a manner that a part of the outer contour (OC) of this extent of the end face abuts an inner contour (IC) of the covering part (CWC).   
     
     
         9 . The arrangement as claimed in  claim 5 ,
 wherein the turbomachine (TM) is of a barrel-type design.