Patent ID: 8047777

Claim:
A turbomachine comprising an annular combustion chamber with a chamber end wall presenting injection orifices having injection systems mounted therein; a compressor having a centrifugal downstream stage; and an annular diffuser enabling the gas flow leaving the compressor to be diffused and directing said flow of gas towards said injection systems, the diffuser comprising: a radially-oriented upstream portion that presents diffusion passages connected to the outlet of the compressor; an elbow-shaped intermediate portion; and a downstream portion comprising a series of circularly spaced apart flow-straightening vanes, the downstream portion being inclined relative to the axis of the turbomachine towards the combustion chamber, in such a manner that in the section plane containing the axis of the turbomachine, the mean axis of the flow path at the outlet from the downstream portion of the diffuser passes through the chamber end wall between the maximum radius and the minimum radius of the chamber end wall; the turbomachine being such that, in the section plane containing the axis of the turbomachine and passing via the center of one of said injection orifices, the curvilinear abscissa distance along a flow line between the middle of the flow path at the trailing edges of the flow-straightening vanes and said center, is greater than or equal to three times the height of said flow path at the trailing edges of the flow-straightening vanes, and such that the number of flow-straightening vanes is at least four times greater than the number of injection systems.