Turbo-engine exhaust gas housing with temperature control device
AssigneeSociete Nationale d'Etude et de Construction de Moteurs d'Aviation "S.N.E.C.M.A."
InventorsMichel S. Guimier, Patrick Kapala, Philippe Paris
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Abstract
A unitary exhaust gas housing for a turbo-engine comprises an outer ring, two intermediate rings defining the flow path for the hot gases, and an inner ring forming a hub with a hollow annular chamber. A temperature control device is provided including a bleed tube having one end fixed and communicating with the gas flow path for drawing off hot gases therefrom, the other end of the tube passing into the hollow chamber of the hub where it regulates the flow of gases by variation of the clearance j between the end of the tube and the opposing wall of the hub in response to relative radial movements of the tube and the hub according to the thermal states of the assembly.
Claims3
A temperature control device in a unitary exhaust gas housing for a turbo-engine comprising an outer ring, two intermediate rings defining the flow path for the hot gases, shaped struts interconnecting said intermediate rings, and an inner ring forming a hub of said housing, said hub defining a closed annular chamber, said temperature control device comprising a bleed tube for drawing off gas from the gas stream in said gas flow path, said tube extending into said closed annular chamber formed by said hub, said tube having a fixed first end in communication with said gas flow path and a second end disposed in said annular chamber, and a wall of said hub spaced from said second end of said tube by a clearance j whereby the flow of gas entering said annular chamber from said gas stream is regulated by variations in said clearance j resulting from radial movements of the tube and the hub relative to one another caused by their thermal state.
Dependencies are inferred from the claim text.