Turbomachine combustion chamber
View Patent ↗An annular combustion chamber for a turbomachine is disclosed. The combustion chamber includes radially internal and radially external cylindrical walls which are fixed by bolting at their upstream ends to an internal and an external annular flange of an annular chamber end wall, and an annular fairing extending in the upstream direction from the chamber end wall. The internal and external annular ends are fixed by bolting to the flanges of the chamber end wall in axial alignment with the annular ends of the walls of the chamber.
1. An annular combustion chamber for a turbomachine, comprising:
radially internal and radially external cylindrical walls with respect to the axis of the turbomachine;
an annular chamber end wall with an internal annular flange and an external annular flange which are bolted to upstream ends of the radially internal and radially external cylindrical walls, respectively; and
an annular fairing extending in the upstream direction from the chamber end wall,
wherein internal and external downstream annular ends of the fairing are fixed by bolting respectively to the internal and external annular flanges of the chamber end wall in axial alignment with upstream annular ends of the internal and external walls of the chamber.
2. The combustion chamber as claimed in claim 1 , wherein the internal and external downstream annular ends of the fairing and internal and external upstream annular ends of the cylindrical walls of the chamber have complementary indentations or undulations which fit into one another, the fixing bolts for connecting the fairing and the cylindrical walls to the chamber end wall passing through the indentations of the fairing and through the indentations of the cylindrical walls.
3. The combustion chamber as claimed in claim 2 , wherein the indentations or undulations comprise an alternation of solid parts and hollow parts, the fixing bolts passing through the solid parts and being distributed in an annular row on the external annular end of the fairing and on the corresponding end of the external wall of the chamber, and an annular row on the internal annular end of the fairing and on the corresponding end of the internal wall of the chamber.
4. The combustion chamber as claimed in claim 3 , wherein each solid part of the indentations or undulations comprises a single fixing bolt through-hole.
5. The combustion chamber as claimed in claim 3 , wherein the solid parts of the indentations or undulations of the ends of the fairing comprise the same number of fixing bolts as the solid parts of the indentations or undulations of the ends of the walls of the chamber.
6. The combustion chamber as claimed in claim 3 , wherein the solid parts of the indentations or undulations of the ends of the fairing comprise a number of fixing bolts that differs from that of the solid parts of the indentations or undulations of the ends of the walls of the chamber.
7. The combustion chamber as claimed in claim 1 , wherein the fixing bolts which connect the external annular end of the fairing and the annular end of the external wall are angularly offset with respect to the fixing bolts which connect the internal annular end of the fairing and the annular end of the internal wall.
8. The combustion chamber as claimed in claim 1 , wherein the annular fairing is made of a single piece or of two annular pieces these respectively being a radially internal and a radially external piece.
9. A turbomachine such as an airplane turbojet or turboprop engine and which comprises an annular combustion chamber as claimed in claim 1 .
10. The combustion chamber as claimed in claim 1 , wherein axial upstream ends of the upstream annular ends of the internal and external walls of the chamber face axial downstream ends of the internal and external downstream annular ends of the fairing, respectively.