US2019376392A1PendingUtilityA1

Gas turbine

42
Assignee: ROLLS ROYCE DEUTSCHLAND LTD & CO KGPriority: Dec 1, 2016Filed: Dec 1, 2017Published: Dec 12, 2019
Est. expiryDec 1, 2036(~10.4 yrs left)· nominal 20-yr term from priority
Inventors:Karl Schreiber
F01D 5/147F01D 5/323F01D 5/3007F05D 2300/6033F01D 5/284F01D 5/3084Y02T50/60
42
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Claims

Abstract

A gas turbine having at least one disk, wherein turbine blade elements are connected via connection means to the at least one disk, wherein the connection means are arranged in the interior of the turbine blade elements in a region radially above the disk in the radial direction of the turbine blade elements, in particular in a region which is in the driving airflow during the operation of the gas turbine, and the turbine blade elements have at least two zones composed of different materials, wherein the at least two zones adjoin one another in particular in the radial direction, and in that a zone with a material suited to compressive stress, in particular a ceramic, in particular an yttrium-stabilized zirconium oxide, is arranged radially below the connection means, and a zone with a material suited to tensile stress, in particular CMSX 4, is arranged radially above the connection means.

Claims

exact text as granted — not AI-modified
1 . A gas turbine having at least one disk, wherein turbine blade elements are connected via connection means to the at least one disk, wherein
 the connection means are arranged in the interior of the turbine blade elements in a region radially above the disk in the radial direction of the turbine blade elements, in particular in a region which is in the driving airflow during the operation of the gas turbine, and   the turbine blade elements have at least two zones composed of different materials, wherein the at least two zones adjoin one another in particular in the radial direction, and   in that a zone with a material suited to compressive stress, in particular a ceramic, in particular an yttrium-stabilized zirconium oxide, is arranged radially below the connection means, and a zone with a material suited to tensile stress, in particular CMSX 4, is arranged radially above the connection means.   
     
     
         2 . The gas turbine as claimed in  claim 1 , wherein the connection means are arranged radially on the inside, radially in the center or radially on the outside in the region radially above the disk, in particular in the region of the turbine blade elements which is in the driving airflow during the operation of the gas turbine. 
     
     
         3 . The gas turbine as claimed in  claim 1 , wherein the connection means are designed for positive joining, nonpositive joining and/or material joining. 
     
     
         4 . The gas turbine as claimed in  claim 3 , wherein the positive connection means have positive joining means, in particular shoulders, projections and/or undercuts for the axial and/or radial fixing of the turbine blade elements. 
     
     
         5 . The gas turbine as claimed in  claim 3 , wherein, in the case of nonpositive connection means, frictional joining can be achieved by means of a wedge connection, in particular in the disk, and/or by means of shrink-fit connections. 
     
     
         6 . The gas turbine as claimed in  claim 3 , wherein, in the case of material connection means, there is a laser-welded joint between the turbine blade elements and the disk. 
     
     
         7 . The gas turbine as claimed in  claim 1 , wherein at least one parting line is arranged between two zones of different material in the turbine blade elements radially below the connection means. 
     
     
         8 . The gas turbine as claimed in  claim 1 , characterized by wedge elements for clamping the disk to the turbine blade elements and/or for producing positive joining between the disk and the turbine blade elements. 
     
     
         9 . The gas turbine as claimed in  claim 1 , wherein the turbine blade elements are connected radially on the outside via a welded joint to the at least one disk. 
     
     
         10 . The gas turbine as claimed in  claim 1 , wherein the turbine blade elements can be assembled from at least two parts. 
     
     
         11 . The gas turbine as claimed in  claim 1 , wherein it is designed as an aircraft engine, as a vehicle propulsion system, as a ship's propulsion system or as a stationary gas turbine. 
     
     
         12 . A turbine blade element or disk, in particular configured and designed for use in a gas turbine as claimed in  claim 1 .

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