| 摘要 |
The invention relates to a turbomachine, more particularly a gas turbine. The turbomachine has a stator and a rotor, wherein the rotor has blades ( 21 ) and the stator has a housing ( 20 ) and stationary guide vanes ( 17 ), wherein the guide vanes ( 17 ) form guide vane rings ( 11, 12 ) that adjoin the housing ( 20 ) with radially outwardly positioned ends ( 18 ) and adjoin the rotor with radially inwardly positioned ends. The guide vane rings are spoke-centered with the aid of bearing journals or guide pins ( 24 ) allocated to the housing ( 20 ) and penetrating through the housing ( 20 ). According to the invention, the guide pins ( 24 ) extend approximately perpendicularly to the housing ( 20 ), wherein the ends ( 26 ) of the guide pins ( 24 ) reaching into the housing engage in forked elements ( 27 ) allocated to the radially outer ends ( 18 ) of the guide vane rings ( 11, 12 ).
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