# US 2016/0258294 A1 · Rotor of a turbine of a gas turbine with improved cooling air routing > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2016/0258294 A1 - Document ID: US20160258294A1 - Status: Published application - Kind: A1 - Application number: 15/059,520 - Filed: 2016-03-03 - Published: 2016-09-08 - Earliest claimed: 2015-03-04 - Assignees: Rolls-Royce Deutschland Ltd & Co KG - Applicants: Rolls-Royce Deutschland Ltd & Co KG - Inventors: Markus WEINERT; Tobias LEYMANN - Web page: https://patentgrep.com/patent/US20160258294A1 ## CPC - F01D 5/081: {Cooling fluid being directed on the side of the rotor disc or at the roots of the blades (F01D5/087 takes precedence)} - F01D 5/10: Anti- vibration means {(specially adapted for radial flow machines or engines F01D5/04)} - F01D 5/22: Blade-to-blade connections, {e.g. for damping vibrations} - F01D 5/225: {by shrouding} - F01D 11/006: {Sealing the gap between rotor blades or blades and rotor} - F05D 2240/55: Seals - F05D 2240/81: Cooled platforms - F05D 2260/201: by impingement of a fluid - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract A rotor of a turbine of a gas turbine, having a rotor hub and a plurality of blade platforms, each carrying at least one turbine blade, and having one each cooling air chamber for passing cooling air formed by adjacent blade platforms. At least one damping element and/or sealing element is arranged radially beneath a platform intermediate gap provided between adjacent blade platforms. The cooling air chamber and/or the platform intermediate gap are designed such that starting from a side of the blade platform facing the adjacent blade platform, at least one outflow pocket open to the platform upper side and connected to the cooling air chamber is formed, and at least one cooling air pocket opened radially inwards to the cooling air chamber is provided in the wall of the cooling air chamber and opens towards the damping element and/or the sealing element or the platform intermediate gap. ## Claims ### Claim 1 Rotor of a turbine of a gas turbine having a turbine rotor hub, on which over the circumference a plurality of blade platforms is arranged, each of which carrying at least one turbine blade, and having one each cooling air chamber for passing through cooling air formed by adjacent blade platforms and a damping element and/or a sealing element, where between adjacent blade platforms at least one damping element and/or sealing element is arranged radially beneath a platform intermediate gap provided between adjacent blade platforms, wherein the resultant cooling air chamber and/or the platform intermediate gap are designed such that starting from a side of the blade platform facing the adjacent blade platform, at least one outflow pocket open to the platform upper side and connected to the cooling air chamber is formed, and that at least one cooling air pocket opened radially inwards to the cooling air chamber is provided in the wall of the cooling air chamber and opens towards the damping element and/or the sealing element or the platform intermediate gap. ### Claim 2 (depends on 1) The rotor in accordance with claim 1, wherein at least one cooling air pocket opened radially inwards to the cooling air chamber is provided exclusively in the wall of the cooling air chamber and opens towards the damping element and/or the sealing element and/or the platform intermediate gap, said cooling air pocket however not being designed in combination with a separate outflow pocket. ### Claim 3 (depends on 1) The rotor in accordance with claim 1, wherein the cooling air pocket is designed convergent or divergent. ### Claim 4 (depends on 1) The rotor in accordance with claim 1, wherein the cooling air pocket is designed at a radial angle parallel or divergent relative to the damping element and/or sealing element. ### Claim 5 (depends on 1) The rotor in accordance with claim 1, wherein the outflow pocket is arranged at a shallow angle or tangentially to the platform upper side. ### Claim 6 (depends on 1) The rotor in accordance with claim 1, wherein the outflow pocket is designed with rounded edges or surfaces freely merging into one another. ### Claim 7 (depends on 1) The rotor in accordance with claim 1, wherein the walls of the cooling air pocket are designed rounded or freely merging into one another. ### Claim 8 (depends on 1) The rotor in accordance with claim 1, wherein one outflow opening of the cooling air pocket of a blade platform is arranged exactly opposite to one inflow opening of the outflow pockets of the adjacent blade platform. ### Claim 9 (depends on 1) The rotor in accordance with claim 1, wherein the outflow pocket has a further outflow pocket in an integral design with predominantly radial orientation. ### Claim 10 (depends on 1) The rotor in accordance with claim 1, wherein over the axial length of the blade platform several outflow pockets are arranged, or one outflow pocket covering the entire length. ### Claim 11 (depends on 1) The rotor in accordance with claim 1, wherein over the axial length of the blade platform several cooling air pockets are arranged. ### Claim 12 (depends on 11) The rotor in accordance with claim 11, wherein the several cooling air pockets are designed partially or completely merging into one another. ### Claim 13 (depends on 1) The rotor in accordance with claim 1, wherein the damping element and/or sealing element is provided with through-flow recesses. ### Claim 14 (depends on 1) The rotor in accordance with claim 1, wherein the outflow pocket and/or the cooling air pocket is provided on a radially outer hot gas platform surface.