US 11,753,963 B2
Method for repairing in-situ installations inside a compressor rear frame case of a gas turbine
Virgil Adam, Arnhem (NL); Glenn L Knight, III, Cincinnati, OH (US); Wiebe Van Der Werff, Arnhem (NL); Valerio Goffi, Florence (IT); and Willem Smit, Ede (NL)
Assigned to General Electric Company, Schenectady, NY (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on Aug. 19, 2020, as Appl. No. 16/997,151.
Claims priority of application No. 18425031 (EP), filed on Apr. 24, 2018.
Prior Publication US 2020/0378272 A1, Dec. 3, 2020
Int. Cl. B23P 6/00 (2006.01); F01D 25/18 (2006.01); B23P 19/04 (2006.01)
CPC F01D 25/18 (2013.01) [B23P 19/042 (2013.01); B23P 6/005 (2013.01); F05D 2230/80 (2013.01); F05D 2260/98 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A method for repairing in-situ a gas turbine having a damaged oil manifold, the gas turbine comprising a compressor, a combustor and a turbine, and a compressor rear frame case between the compressor and the turbine, wherein the combustor, a front end bearing assembly, and an aft end bearing assembly are located inside the compressor rear frame case,
wherein the front end bearing assembly includes at least one axial bearing and at least one radial bearing, and the aft end bearing assembly includes at least one radial bearing, the front end bearing assembly further including a front end bearing housing, and the aft end bearing assembly including an aft end bearing housing,
wherein the compressor comprises a rotor with a bearing journal at least on an outlet end of the compressor that is borne by the at least one radial bearing inside the front end bearing assembly,
wherein the turbine comprises a rotor with a bearing journal on at least an inlet end of the turbine rotor that is borne by the at least one radial bearing in the aft end bearing assembly,
wherein the bearing journal at the outlet end of the compressor rotor and the bearing journal at the inlet end of the turbine rotor are detachably connected, and wherein the damaged oil manifold is attached to a forward sump housing for feeding oil to the front end bearing assembly, the method comprising the steps of:
a) removing the turbine from the compressor rear frame case while leaving the compressor rear frame case installed in the gas turbine;
b) removing the aft end bearing housing from the compressor rear frame case while leaving the compressor rear frame case installed in the gas turbine;
c) removing an aft sump assembly from the compressor rear frame case while leaving the compressor rear frame case installed in the gas turbine, the aft sump assembly including an aft sump housing;
d) removing the damaged oil manifold, an oil supply, and air tubes from the compressor rear frame case while leaving the compressor rear frame case installed in the gas turbine;
e) removing a sump closure and a lube oil nozzle;
f) installing a replacement oil manifold to the aft sump assembly, wherein the replacement oil manifold is one of a repaired oil manifold or a new oil manifold;
i) installing the aft sump assembly and a bearing closure;
j) installing the aft end bearing housing to the compressor rear frame case, and
k) installing the turbine to the compressor rear frame case.