Patent ID: 7549294
Filing Date: 2009-06-23
Classification: F23C,F23R

Abstract:
1. A turbomachine assembly comprising: an annular compression section for compressing air passing through said turbomachine; a turbomachine casing formed by an outer annular shell centered on a longitudinal axis (X-X) of the turbomachine and an inner annular shell secured coaxially inside the outer shell by a plurality of radial support arms; an annular combustion section housed inside the turbomachine casing, disposed at the outlet from the compression section and within which the air coming from the compression section is mixed with fuel in order to be burnt therein; and an annular turbine section disposed at the outlet from the combustion section and having a plurality of moving wheels that are driven in rotation by the gas coming from the combustion section, the air coming from the compression section presenting rotary motion with an angle of inclination relative to the longitudinal axis (X-X) of the turbomachine; wherein each of the support arms presents an angle of inclination (α) relative to the longitudinal axis (X-X) of the turbomachine that is substantially equal to or greater than the angle of inclination of the air coming from the compression section so as to impart to the gas coming from the combustion section rotary motion with an angle of inclination that is substantially equal to or greater than the angle of inclination of the air coming from the compression section.