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Apparatus and method for reducing thermal stress in a turbine rotor
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1978 |
| Description | A gas turbine is described wherein the thermal stresses in the turbine rotor are reduced. The rotor includes a central disc with a peripheral rim, and a plurality of blades extending radially outward from the rim. To reduce thermal stresses, a duct arrangement is provided which selectively directs hot gases from the turbine combustor to the rim during the turbine start up. The hot gases from the combustor serve to heat the rim, and decrease the start up period necessary to bring the temperature profile of the rotor into the operating temperature range. After the start up period, the duct arrangement is then used to direct cool gases from the turbine compressor to the rim of the rotor in order to maintain a lower rotor equilibrium temperature. |
| File Size | 450052 |
| Page Count | 6 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19790001886 |
| Archival Resource Key | ark:/13960/t6159cz2z |
| Language | English |
| Publisher Date | 1978-10-03 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Propulsion And Power Turbocompressors Gas Turbines Rotor Blades High Temperature Gases Temperature Profiles Combustion Chambers Thermal Stresses Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Patent |
