Annular gas turbine housing component and a gas turbine comprising the component

Abstract

The invention relates to an annular gas turbine housing component ( 15 ) comprising a plurality of circumferentially spaced first channels ( 16 ) for conveying a first gas flow in a first direction and a plurality of circumferentially spaced second channels ( 17 ) for conveying a second gas flow in a second direction across the first direction in a crossing position ( 18 ) of the first and second channels.

1 . An annular gas turbine housing component comprising a plurality of circumferentially spaced first channels for conveying a first gas flow in a first direction, and a plurality of circumferentially spaced second channels for conveying a second gas flow in a second direction across the first direction in a crossing position of the first and second channels. 
     
     
         2 . A gas turbine housing component according to  claim 1 , wherein a plurality of the first channels alternate with a plurality of the second channels in the circumferential direction. 
     
     
         3 . A gas turbine housing component according to  claim 1 , wherein every other channel in the circumferential direction is a first channel and every other channel in the circumferential direction is a second channel at least along a portion of the circumference. 
     
     
         4 . A gas turbine housing component according to  claim 1 , wherein the component comprises a wall structure, which comprises a plurality of circumferentially spaced radial walls, which define the first channels and second channels. 
     
     
         5 . A gas turbine housing component according to  claim 4 , wherein the wall structure is configured so that each of the radial walls define one of the first channels on one side and one of the second channels on the other side in the circumferential direction at least along a portion of the circumference. 
     
     
         6 . A gas turbine housing component according to  claim 1 , wherein at least a plurality of the first channels are configured so that there is an increase in their radial extension from a position upstream the crossing position in a gas flow direction to the crossing position. 
     
     
         7 . A gas turbine housing component according to  claim 1  wherein the plurality of first channels are configured so that a flow path area in the crossing position is at least as large as in a position upstream the crossing position in a gas flow direction. 
     
     
         8 . A gas turbine housing component according to  claim 1 , wherein the plurality of first channels are configured so that a flow path area in a position upstream the crossing position in a gas flow direction is substantially the same as in the crossing position. 
     
     
         9 . A gas turbine housing component according to  claim 1  wherein the component comprises a circumferentially substantially continuous gas flow channel, which is divided into the plurality of circumferentially spaced first channels. 
     
     
         10 . A gas turbine housing component according to  claim 9 , wherein an axial position of the channel division is about at the same axial position as the upstream position. 
     
     
         11 . A gas turbine housing component according to  claim 10 , wherein a center line of the continuous gas flow channel in a radial direction in the upstream position is positioned on substantially the same radial position as a center line of the plurality of circumferentially spaced first channels in the crossing position. 
     
     
         12 . A gas turbine housing component according to  claim 1 , characterized in that the first channels are configured for conveying the first gas flow substantially in an axial direction ( 2 ) of the component. 
     
     
         13 . A gas turbine housing component according to  claim 1 , wherein the plurality of second channels are configured for conveying the second gas flow substantially in a radial direction of the component. 
     
     
         14 . A gas turbine housing component according to  claim 1 , wherein the component is configured for a channel loop connecting the first channels to the second channels so that a gas flow from the first channels subsequently will flow through the second channels in gas turbine operation. 
     
     
         15 . A gas turbine housing component according to  claim 14 , wherein heat exchanger is positioned in the loop for cooling the gas flow. 
     
     
         16 . A gas turbine housing component according to  claim 1 , wherein the first gas flow channel defines a primary gas flow channel. 
     
     
         17 . A gas turbine wherein it comprises a gas turbine housing component according to  claim 1 . 
     
     
         18 . A gas turbine according to  claim 17 , wherein the component is arranged so that uncombusted air is conveyed via the second channels during operation. 
     
     
         19 . A gas turbine according to  claim 17 , wherein the component is arranged so that the second gas flow in the second channels flows from a radially outer position to a radially inner position in relation to the crossing point during operation. 
     
     
         20 . A gas turbine according to  claim 17 , wherein the gas turbine comprises a channel loop connecting the first channels to the second channels so that a gas flow from the first channels subsequently will flow through the second channels in gas turbine operation. 
     
     
         21 . A gas turbine according to  claim 20 , wherein the gas turbine is configured to cool the gas flow in the loop during operation. 
     
     
         22 . A gas turbine according to  claim 17 , wherein it comprises at least two axially spaced compressor stages and that the gas turbine housing component is positioned between the compressor stages so that a gas flow from a first compressor stage will enter the first channels and the gas flow from the second channels will enter a second compressor stage in operation. 
     
     
         23 . A gas turbine according to  claim 22  wherein a downstream end of the first compressor stage is positioned on a substantially larger radial distance than an upstream end of the second compressor stage. 
     
     
         24 . An annular gas turbine housing component comprising a plurality of circumferentially spaced first channels for conveying a first gas flow in a first direction, wherein the component comprises a plurality of circumferentially spaced second channels for conveying a second gas flow in a second direction across the first direction in a crossing position of the first and second channels. 
     
     
         25 . A gas turbine housing component according to  claim 24 , wherein a plurality of the first channels alternate with a plurality of the second channels in the circumferential direction. 
     
     
         26 . A gas turbine housing component according to  claim 24 , wherein every other channel in the circumferential direction is a first channel and every other channel in the circumferential direction is a second channel at least along a portion of the circumference. 
     
     
         27 . A gas turbine housing component according to  claim 24 , wherein the component comprises a wall structure, which comprises a plurality of circumferentially spaced radial walls, which define the first channels and second channels. 
     
     
         28 . A gas turbine housing component according to  claim 27 , wherein the wall structure is configured so that each of the radial walls define one of the first channels on one side and one of the second channels on the other side in the circumferential direction at least along a portion of the circumference. 
     
     
         29 . A gas turbine housing component according to  claim 24 , wherein at least a plurality of the first channels are configured so that there is an increase in their radial extension from a position upstream the crossing position in a gas flow direction to the crossing position. 
     
     
         30 . A gas turbine housing component according to  claim 24 , wherein the plurality of first channels are configured so that a flow path area in the crossing position is at least as large as in a position upstream the crossing position in a gas flow direction. 
     
     
         31 . A gas turbine housing component according to  claim 24 , wherein the plurality of first channels are configured so that a flow path area in a position upstream the crossing position in a gas flow direction is substantially the same as in the crossing position. 
     
     
         32 . A gas turbine housing component according to  claim 24 , wherein the component comprises a circumferentially substantially continuous gas flow channel, which is divided into the plurality of circumferentially spaced first channels. 
     
     
         33 . A gas turbine housing component according to  claim 32 , wherein an axial position of the channel division is about at the same axial position as the upstream position. 
     
     
         34 . A gas turbine housing component according to  claim 33 , wherein a center line of the continuous gas flow channel in a radial direction in the upstream position is positioned on substantially the same radial position as a center line of the plurality of circumferentially spaced first channels in the crossing position. 
     
     
         35 . A gas turbine housing component according to  claim 24 , wherein the first channels are configured for conveying the first gas flow substantially in an axial direction of the component. 
     
     
         36 . A gas turbine housing component according to  claim 24 , wherein the plurality of second channels are configured for conveying the second gas flow substantially in a radial direction of the component. 
     
     
         37 . A gas turbine housing component according to  claim 24 , wherein the component is configured for a channel loop connecting the first channels to the second channels so that a gas flow from the first channels subsequently will flow through the second channels in gas turbine operation. 
     
     
         38 . A gas turbine housing component according to  claim 37 , wherein heat exchanger is positioned in said the loop for cooling the gas flow. 
     
     
         39 . A gas turbine housing component according to  claim 24 , wherein the first gas flow channel defines a primary gas flow channel. 
     
     
         40 . A gas turbine wherein it comprises a gas turbine housing component according to  claim 24 . 
     
     
         41 . A gas turbine according to  claim 40 , wherein the component is arranged so that uncombusted air is conveyed via the second channels during operation. 
     
     
         42 . A gas turbine according to  claim 40 , wherein the component is arranged so that the second gas flow in the second channels flows from a radially outer position to a radially inner position in relation to the crossing point during operation. 
     
     
         43 . A gas turbine according to  claim 40 , wherein the gas turbine comprises a channel loop connecting the first channels to the second channels so that a gas flow from the first channels subsequently will flow through the second channels in gas turbine operation. 
     
     
         44 . A gas turbine according to  claim 43 , wherein the gas turbine is configured to cool the gas flow in the loop during operation. 
     
     
         45 . A gas turbine according to  claim 40 , wherein it comprises at least two axially spaced compressor stages and that the gas turbine housing component is positioned between the compressor stages so that a gas flow from a first compressor stage will enter the first channels and the gas flow from the second channels will enter a second compressor stage in operation. 
     
     
         46 . A gas turbine according to  claim 45  wherein a downstream end of the first compressor stage is positioned on a substantially larger radial distance than an upstream end of the second compressor stage.