HIGH PRESSURE TURBINE DISK WITH REDUCED AXIAL STRESS AND METHOD FOR REDUCING AXIAL STRESS
PROBLEM TO BE SOLVED: To provide a high pressure turbine disk hub with reduced axial stress and a method for reducing axial stress. SOLUTION: A gas turbine engine disk that includes centrally disposed disk hubs 21, 24, 56, 74, 94, 114 having integrally-formed, radially outwardly extending webs 18, 2...
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| creator | KULESA JOSEPH CHARLES HIGGINS CRAIG WILLIAM ENGLAND CHARLES CHRIS LAMMAS ANDREW J |
| description | PROBLEM TO BE SOLVED: To provide a high pressure turbine disk hub with reduced axial stress and a method for reducing axial stress. SOLUTION: A gas turbine engine disk that includes centrally disposed disk hubs 21, 24, 56, 74, 94, 114 having integrally-formed, radially outwardly extending webs 18, 20, 72, 92, 112 terminating at an outer end. The disk hubs 21, 24, 56, 74, 94, 114 have radially-displaced annular hub surfaces 76, 96, 116, 166 exposed to high pressure, high temperature discharge gases during engine operation. The radially-displaced annular hub surfaces 76, 96, 116, 166 act as an axial free surface mitigating the formation undesirable axial stress in the disk hubs 21, 24, 56, 74, 94, 114. COPYRIGHT: (C)2007,JPO&INPIT |
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SOLUTION: A gas turbine engine disk that includes centrally disposed disk hubs 21, 24, 56, 74, 94, 114 having integrally-formed, radially outwardly extending webs 18, 20, 72, 92, 112 terminating at an outer end. The disk hubs 21, 24, 56, 74, 94, 114 have radially-displaced annular hub surfaces 76, 96, 116, 166 exposed to high pressure, high temperature discharge gases during engine operation. The radially-displaced annular hub surfaces 76, 96, 116, 166 act as an axial free surface mitigating the formation undesirable axial stress in the disk hubs 21, 24, 56, 74, 94, 114. COPYRIGHT: (C)2007,JPO&INPIT</abstract><oa>free_for_read</oa></addata></record> |
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| subjects | AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TOTRANSPORTATION COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS INDEXING SCHEME FOR ASPECTS RELATING TONON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES ORJET-PROPULSION PLANTS INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUSSUBCLASSES OF CLASSES F01-F04 LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINSTCLIMATE CHANGE WEAPONS |
| title | HIGH PRESSURE TURBINE DISK WITH REDUCED AXIAL STRESS AND METHOD FOR REDUCING AXIAL STRESS |
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