Turbine Wheel Arrangement For A Gas Turbine

Abstract

The invention relates to a turbine wheel arrangement for a gas turbine comprising two successive turbine wheels ( 18, 20 ) rotating in opposite directions, wherein the first turbine wheel ( 18 ) comprises flow channels ( 42 ) of a Laval cross-sectional shape, distributed over the circumference and having radially inner gas inlets ( 43 ) and radially further out gas outlets ( 45 ), in each case with a substantially tangential flow direction component, wherein the gas outlets ( 45 ) act an the second axially or radially acting turbine wheel ( 20 ) in the direction of flow. This has the effect that the thermal energy and compressive energy of the gas at the nozzle inlet is largely converted into flow energy at the outlet of the turbine stage. The rotational speeds of the two rotors coupled to the turbine wheels can be set as desired, allowing the operational states of the two systems to be optimally set without adjusting systems.

1 . A gas turbine comprising a first turbine wheel and a second turbine wheel rotating in the opposite direction which is impacted by the first turbine wheel, further comprising an inner shaft on the outside of which multiple first blade rows of a multi-stage axial compressor and the second turbine wheel are mounted, further comprising a hollow shaft on which the first turbine wheel and multiple second blade rows of the axial compressor are mounted, which are arranged alternatingly in the axial direction relative to the first blade rows. 
     
     
         2 . The gas turbine according to  claim 1 , wherein the first turbine wheel comprises flow channels distributed over the circumference thereof, which include gas outlets of a laval cross-sectional shape. 
     
     
         3 . The gas turbine according to  claim 2 , wherein the gas outlets include a substantially tangential flow direction component. 
     
     
         4 . The gas turbine according to  claim 3 , wherein the gas outlets of the first turbine wheel are oriented at an angle of 10° to 30° relative to the tangential direction. 
     
     
         5 . The gas turbine according to  claim 1 , wherein at least one rotating combustion chamber is mounted on the hollow shaft. 
     
     
         6 . The gas turbine according to  claim 1 , wherein the flow channels exhibit a Laval nozzle-like cross-section in one transverse direction of the flow and no variation in cross-section in the other transverse direction of the flow. 
     
     
         7 . The gas turbine according to  claim 2 , wherein the first turbine wheel comprises a disk to which shaped pieces distributed over the circumference thereof are molded or attached, between which the flow channels of Laval cross-sectional shape are formed. 
     
     
         8 . The gas turbine according to  claim 1 , wherein the second turbine wheel in the direction of flow includes Pelton turbine blades. 
     
     
         9 . The gas turbine according to  claim 1 , wherein the second turbine wheel is an axial turbine wheel. 
     
     
         10 . The gas turbine according to  claim 1 , wherein the second turbine wheel is a radial turbine wheel. 
     
     
         11 . The gas turbine according to  claim 1 , wherein each flow channel of Laval cross-sectional shape is associated with a co-rotating combustion chamber. 
     
     
         12 . The gas turbine according to  claim 1 , wherein a radial compressor is mounted on the hollow shaft downstream of the axial compressor. 
     
     
         13 . The gas turbine according to  claim 1 , wherein the rotor of the first generator is mounted on the inner rotor and the rotor of the second generator is mounted on the outside of the hollow shaft. 
     
     
         14 . The gas turbine according to  claim 1 , wherein by controlling the two generators the rotational speed of the two turbine wheels can be set as desired, allowing the operational states of the two systems to be optimally set without adjusting systems.