Snecma

Michel Andre Albert Desaulty

Denis Jean Maurice Sandelis

Alain Rene Cayre

Romain Nicolas Lunel

Patrice Andre Commaret

Nicolas Pommier

Michel Pierre Cazalens

Olivier Kreder

Pascale Rollet

Christophe Baudoin

A turbomachine comprising an annular combustion chamber () with injection orifices (); a centrifugal compressor () having a centrifugal downstream stage and an annular diffuser () comprising: a radially-oriented upstream portion ()with diffusion passages () connected to the outlet of the compressor and an elbow-shaped intermediate portion ()and a downstream portion () comprising a series of flow-straightening vanes () and inclined relative to the axis (A) of the turbomachine. In the section plane containing the axis (A) of the turbomachine and passing via the center (C) of one of said injection orifices (), the curvilinear abscissa distance along a flow line (L) between the middle (0) of the flow path at the trailing edges of the flow-straightening vanes () and said center (C) is greater than or equal to three times the height (h) of said flow path.

Turbomachine diffuser

A fuel injector system for injecting fuel into a turbomachine combustion chamber, the system comprising first and second fuel injectors wherein the first injector () is positioned in the center of the injector system () so as to inject a first fuel spray (), and wherein the second injector () surrounds the first injector in such a manner as to inject a second fuel spray () of generally annular shape around the first fuel spray. The injector system further comprises an air admission duct () with outlet orifices () opening out between the first and second injectors so as to create a separator air film (f) between the respective combustion zones of the first and second fuel sprays.

Dual-injector fuel injector system

A device for injecting a mixture of air and fuel into a combustion chamber of a turbomachine is disclosed. The injection device includes a novel sliding bushing and a novel annular cup for retaining the sliding bushing, making it possible to improve the air feed of the injection device.

Device for injecting a mixture of air and fuel, and combustion chamber and turbomachine provided with such a device

A gas turbine engine diffuser defined between an external casing and an internal casing of the engine and supplied with air via an upstream annular diffuser duct is disclosed. The diffuser includes a combustion chamber of the convergent type, forming an external annular duct with the external casing and an internal annular duct with the internal casing, and a cowling partially closing off the external annular duct. The cowling is positioned toward the closed end of the combustion chamber.

Gas turbine engine diffuser and combustion chamber and gas turbine engine comprising same

A shroud for a combustion chamber bottom designed to cover fuel injectors is provided with drillings on at least one of its sides to open up the cavity within the shroud and reduce noise that it produces and combustion instabilities. The drillings also have the effect of reducing instabilities and non-uniformity of the airflow around the shroud.

Shroud for a turbomachine combustion chamber

The invention relates to a device for injecting a mixture of air and fuel into a combustion chamber of a turbomachine where the supply of air is improved. The invention relates more particularly to a new type of sliding bushing.

Growing community of inventors

Vert St Denis, France

Michel Andre Albert Desaulty