F - Mech Eng,Light,Heat,Weapons – 02 – C
Patent
F - Mech Eng,Light,Heat,Weapons
02
C
170/67
F02C 7/12 (2006.01) F01D 5/18 (2006.01) F01D 25/12 (2006.01)
Patent
CA 1116094
13DV-7278 TURBINE BAND COOLING SYSTEM Abstract A gas turbine engine comprising a number of annular wall sectors which form a complete circular wall defining a hot gas passage is provided with a cooling system incorporating a plurality of hollow impinge- mint vessels disposed in a circular array within an annular chamber behind the wall. Cooling fluid is routed to the self-contained impingement pressure vessels which are provided with perforations to disperse the cooling fluid into impingement upon the wall. Unlike prior systems, the impingement vessels are not physically attached to the band but, rather, are supported by a structural frame which partially defines the annular chamber and, in the preferred embodiment, also supports the wall sectors. Since the impingement vessel, and not the backside of the wall, is the pressure vessel for the pres- surized cooling fluid, leakage between adjacent wall sectors is greatly reduced with no loss in cooling effectiveness when compared to conventional cooling systems. Thus, turbine cycle performance is improved.
323488
Auxier Thomas A.
Landis Delmer H.
Lievestro Louis
Lozier Paul W.
Starkweather John H.
Company General Electric
Eckersley Raymond A.
LandOfFree
Turbine band cooling system does not yet have a rating. At this time, there are no reviews or comments for this patent.
If you have personal experience with Turbine band cooling system, we encourage you to share that experience with our LandOfFree.com community. Your opinion is very important and Turbine band cooling system will most certainly appreciate the feedback.
Profile ID: LFCA-PAI-O-353892