Volute with two chambers for a gas turbine

Abstract

A volute ( 10 ) with two chambers for a gas turbine ( 50 ), including a circumferential conduit ( 11 ) in the form of a spiral, a first opening ( 12 ) oriented tangentially to the said circumferential conduit ( 11 ), toward the outside of the said circumferential conduit ( 11 ), and a second circumferential opening ( 13 ) located at the center of the said circumferential conduit ( 11 ). A wall ( 15 ) separates the said circumferential conduit ( 11 ) into two symmetrical chambers ( 18 ) ( 19 ), with a first fluid and a second fluid being able to circulate independently and in an isolated manner between the said first opening ( 12 ) and the said second opening ( 13 ). The said first opening ( 12 ) allows a linear flow of the two fluids between the said circumferential conduit ( 11 ) and a chamber exterior to the said circumferential conduit ( 11 ), while the said second opening ( 13 ) allows a radial flow of the said two fluids between the said circumferential conduit ( 11 ) and a chamber interior to the said circumferential conduit ( 11 ).

What is claimed is: 
     
         1 . A volute with two chambers for a gas turbine, including:
 a circumferential conduit in the form of a spiral,   a first opening oriented tangentially to the said circumferential conduit, toward the outside of the said circumferential conduit, and   a second circumferential opening located at the center of the said circumferential conduit,   wherein said volute with two chambers includes a wall separating the said circumferential conduit into two separate chambers, with a first fluid and a second fluid being able to circulate independently and in an isolated manner between the said first opening and the said second opening.   
     
     
         2 . A volute with two chambers according to  claim 1 , wherein said circumferential conduit is in the form of a water droplet. 
     
     
         3 . A volute with two chambers according to  claim 1 , wherein said two chambers are equal and symmetrical. 
     
     
         4 . A volute with two chambers according to  claim 1 , wherein said wall allows a thermal exchange between a first fluid and a second fluid circulating respectively in the said two chambers of the said circumferential conduit. 
     
     
         5 . A volute with two chambers according to  claim 1 , wherein blades are provided in the said second circumferential opening in order to facilitate the conversion between a radial flow of a fluid in the said second opening and a tangential flow of the said fluid in the said circumferential conduit. 
     
     
         6 . A volute with two chambers according to  claim 1 , wherein said volute with two chambers includes a diffuser located inside the said circumferential conduit and upstream of the said second opening for a fluid entering through the said second opening. 
     
     
         7 . A volute with two chambers according to  claim 6 , wherein blades are provided in the said diffuser in order to facilitate the conversion between a radial flow of a fluid in the said second opening and a tangential flow of the said fluid in the said circumferential conduit. 
     
     
         8 . A gas turbine including:
 a compressor;   a combustion chamber;   an expansion turbine for burned gases;   a heat exchanger allowing exhaust gas to heat compressed air leaving the compressor prior to injection into the combustion chamber, the heat exchanger including an inlet conduit and an outlet conduit for the compressed air; and   an exhaust duct;   wherein said gas turbine includes a volute with two chambers according to  claim 1 , with the first opening being linked to the inlet and outlet conduits; with the said second opening being linked to the compressor and to the combustion chamber; with the first chamber being linked to the compressor and to the inlet conduit; and with the second chamber being linked to the outlet conduit and to the combustion chamber.   
     
     
         9 . A gas turbine according to  claim 8 , wherein said heat exchanger is positioned in series with the said compressor, the said combustion chamber, and the said expansion turbine. 
     
     
         10 . A gas turbine according to  claim 8 , wherein said heat exchanger is positioned in parallel with the said compressor, the said combustion chamber, and the said expansion turbine. 
     
     
         11 . A rotary-wing aircraft wherein said aircraft includes at least one gas turbine according to  claim 8 .