Paprotna
Hubert Paprotna, Palm City, FL US
Patent application number | Description | Published |
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20120057969 | RING SEGMENT WITH IMPINGEMENT AND CONVECTIVE COOLING - A ring segment for a gas turbine engine includes an outer panel defining a structural body for the ring segment. An outer side of an inner panel is attached to an inner side of the outer panel at an interface, and an inner side of the inner panel defines a portion of a hot gas path through the gas turbine engine. An outer side of the outer panel, opposite from the interface, is in communication with a source of cooling air. A plurality of impingement holes extend through the outer panel from the outer side to the inner side of the outer panel for directing impingement air to the outer side of the inner panel. The outer and inner panels define a plurality of flow channels at the interface for effecting convective cooling of the outer panel along the flow channels between the outer and inner panels. | 03-08-2012 |
Hubert E. Paprotna, Palm City, FL US
Patent application number | Description | Published |
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20090142189 | ABRADABLE LABYRINTH TOOTH SEAL VANE SHROUD THROUGH FLOW-PLATFORM COVER - A seal assembly ( | 06-04-2009 |
Hubertus E. Paprotna, Palm City, FL US
Patent application number | Description | Published |
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20090263243 | Combustion Turbine Including a Diffuser Section with Cooling Fluid Passageways and Associated Methods - A combustion turbine includes a compressor section, a combustion section downstream from the compressor section, and a turbine section downstream from the combustion section. A diffuser section is downstream from the turbine section and has an outer wall, an inner wall, and at least one strut member extending therebetween. The outer wall has at least one first gas passageway therein, the inner wall has at least one second gas passageway therein, and the at least one strut member has at least one third gas passageway therein. The at least one first, second and third gas passageways deliver gas therethrough to assist attachment of a boundary layer to adjacent surfaces of the outer wall, the inner wall, and the at least one strut, respectively. | 10-22-2009 |
20110070078 | Cover Assembly for Gas Turbine Engine Rotor - A cover assembly disposed about a rotor in a gas turbine engine. The cover assembly comprises a first cover, a second cover, and securing structure. The first cover is disposed about the rotor and comprises a forward end and an opposed aft end. The first cover is associated with a case mounting structure that is fixed to an engine casing. The second cover is disposed about the rotor and comprises a forward end and an opposed aft end. At least a portion of the first cover is disposed radially outwardly from the second cover. The securing structure couples the first cover to the second cover and permits relative radial movement between the first and second covers. | 03-24-2011 |