The invention relates to a rotor (10) for a turbo machine, in particular for an aircraft turbine, having rotating blades (12), which are joined with a basic rotor body (16) and, radially underneath their blade platforms (18), comprise channels (22) for introducing cooling air (KL) into rotating blad
The invention relates to a rotor (10) for a turbo machine, in particular for an aircraft turbine, having rotating blades (12), which are joined with a basic rotor body (16) and, radially underneath their blade platforms (18), comprise channels (22) for introducing cooling air (KL) into rotating blades (12), whereby a gas diffusor (24) is provided on a high-pressure (HD) side of rotor (10), this diffusor being designed to at least reduce a hot-gas (HL) flow into channels (22) during the operation of the associated turbo machine and to permit an entry of cooling air (KL) into channels (22), whereby gas diffusor (24) is joined to rotor (10) and comprises a blocking element (28) running annularly in the circumferential direction of rotor (10). A related method for manufacturing, repairing and/or overhauling a rotor (10) for a turbo machine is also provided.
대표청구항▼
1. A rotor (10) for a turbo machine, in particular for an aircraft turbine, having rotating blades (12) that are joined to a basic rotor body (16) and, radially underneath blade platforms (18), comprise channels (22) for introducing cooling air (KL) into the rotating blades (12), a gas diffusor (24)
1. A rotor (10) for a turbo machine, in particular for an aircraft turbine, having rotating blades (12) that are joined to a basic rotor body (16) and, radially underneath blade platforms (18), comprise channels (22) for introducing cooling air (KL) into the rotating blades (12), a gas diffusor (24) being provided on the high-pressure (HD) side of rotor (10), the diffusor being designed to at least reduce a hot-gas (HL) flow into channels (22) during the operation of the associated turbo machine and to permit the entry of cooling air (KL) into channels (22), is characterized in that gas diffusor (24) is joined to rotor (10) and comprises a blocking element (28) running annularly in the circumferential direction of rotor (10), this element being disposed between undersides of radially inner blade shrouds (17) of rotating blades (12) and a region connecting rotating blades (12) to basic rotor body (16), for reducing the hot gas (HL) flow; wherein the blocking element (28) covers between 20% and 90% of the inlet surfaces of channels (22). 2. The rotor (10) according to claim 1, wherein the blocking element (28) is joined to the undersides of the radially inner blade shrouds (17) of rotating blades (12) and/or comprises several blocking element segments (26) formed in one piece with rotating blades (12) and/or is fixed in the region joining rotating blades (12) to basic rotor body (16). 3. The rotor (10) according to claim 2, wherein the blocking element (28) is joined cohesively and/or in a form-fitting manner and/or in a force-fitting manner with the undersides of the radially inner blade shrouds (17). 4. The rotor (10) according to claim 1, wherein the blocking element (28) covers between 30% and 60% of the inlet surfaces of channels (22). 5. The rotor (10) of claim 1, wherein the blocking element (28) comprises at least one through-opening (34), by means of which cooling air can enter into channels (22). 6. The rotor (10) according to claim 5, wherein, in each case, a through-opening (34) is provided for at least two adjacent channels (22). 7. The rotor (10) according to claim 1, wherein the gas diffusor (24) comprises at least one securing element (32) for preventing a relative axial and/or radial movement of blocking element (28) in relation to basic rotor body (14). 8. The rotor (10) according to claim 1, wherein the gas diffusor (24) is balanced by at least one of a positive mass balance and a negative mass balance, wherein the positive mass balance comprises balancing weights attached to the gas diffusor; andwherein the negative mass balance comprises areas in which mass has been removed from the gas diffusor. 9. The rotor (10) according to claim 8, wherein the balancing device (36) comprises a plurality of recesses (38) for inserting balancing weights, these recesses being distanced from one another in the circumferential direction and/or disposed radially underneath the joining region of rotating blades (12). 10. The rotor (10) according to claim 1, wherein the gas diffusor (24) and/or at least the blocking element (28) consist(s) of a material that is resistant to high temperatures, in particular a nickel-based alloy and/or a titanium aluminide. 11. The rotor (10) according to claim 1, wherein the blocking element (28) comprises at least one contact surface (30) for the axial and/or radial contact to basic rotor body (16) and/or to rotating blades (12). 12. The rotor (10) according to claim 1, wherein the rotating blades (12) are one of: joined to the basic rotor body (16) in a detachable manner and joined to the basic rotor body (16) cohesively. 13. The rotor (10) according to claim 1, wherein the rotor (10) is configured for use in a turbo machine. 14. A method for manufacturing, repairing and/or overhauling a rotor (10) for a turbo machine, in particular for an aircraft turbine, in which a gas diffusor (24) is joined in a torsionally rigid manner to rotor (10) on the high-pressure (HD) side of rotor (10), wherein gas diffusor (24) comprises a blocking element (28) running annularly in the circumferential direction of rotor (10), the blocking element being disposed between undersides of radially inner blade shrouds (17) of rotating blades (12) and a region connecting rotating blades (12) to a basic rotor body (16) of rotor (10), and the blocking element permitting a hot-gas (HL) flow to be at least reduced in channels (22), which are formed radially underneath blade platforms (18) of rotating blades (12) for introducing cooling air (KL), as well as permitting the entry of cooling air (KL) into channels (22), during the operation of the turbo machine; wherein the blocking element (28) covers between 20% and 90% of the inlet surfaces of channels (22). 15. The method according to claim 14, wherein the gas diffusor (24) is shrunk-fit onto basic rotor body (16) and/or joined cohesively with the undersides of the radially inner blade shrouds (17) of rotating blades (12) and/or is riveted to rotor (10).
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