当前申请(专利权)人地址：
Stadtbachstraße 1, 86153, Augsburg, Germany
摘要：
A gas turbine combustion chamber 10 has a combustion chamber housing 11 and a burner 12, with at least a portion of the burner positioned in the combustion chamber housing. A flame tube 15 is also positioned in the combustion chamber housing, and the flame tube provides a primary combustion zone 16 of the gas turbine combustion chamber. A flame tube cover 17 is positioned on an upstream end of the flame tube and an adjacent mixing tube 19 extends radially and adjoins the flame tube cover. An axial air flow passage 20 is formed between the mixing tube and the flame tube cover, and in use, the axial air flow passage conducts cooling air in an axial direction outside and along the mixing tube. Radial air flow ducts 22 are provided in the flame tube cover and conduct the air following the axial air flow passage to cool the flame tube cover. The radial air flow ducts in the flame tube cover may follow a curved or spiral pathway (22 Fig 2), and a seal 28 may be provided between the mixing tube and flame tube cover. The improved cooling increases the lifespan of the combustion chamber.
权利要求：
Claims
9. A gas turbine combustion chamber (10), comprising:
a combustion chamber housing (11);
a burner (12), at least a portion of which is positioned in the combustion chamber housing (11); and
a flame tube (15) positioned in the combustion chamber housing (11), the flame tube (15) defining a primary combustion zone (16) of the gas turbine combustion chamber (10),
wherein a flame tube cover (17) is positioned on an upstream end of the flame tube (15),
wherein a mixing tube (19) of the burner (12) extends in a region radially inside and adjoining the flame tube cover (17), at least a portion of the mixing tube (19) defining a pre-primary combustion zone (21) of the gas turbine combustion chamber (10),
wherein an axial air flow passage (20) is formed between the mixing tube (19) of the burner (12) and the flame tube cover (17), the axial air flow passage (20) configured to conduct air in an axial direction outside and along the mixing tube (19) for cooling the mixing tube (19), and
wherein radial air flow ducts (22) are provided in the flame lid (17), the radial air flow ducts (22) configured to conduct the air following the axial air flow passage (20) in a radial direction of the flame tube cover (17) for cooling the flame tube cover (17).
2 The gas turbine combustion chamber according to Claim 1, wherein inlet openings (24) of the radial air flow ducts (22) are formed on a radially inner lateral surface (23) of the flame tube cover (17), the inlet openings (24) configured to pass the air from the axial air flow passage (20) into the radial air flow passages (22).
3. The gas turbine combustion chamber according to Claim 1 or 2, wherein outlet openings of the radial air flow passages (22) are formed on an axial surface
(18) of the flame tube cover (17) facing the primary combustion zone (16), via which outlet openings the air exits from the radial air flow passages (22) and enters the primary combustion zone (16).
4. The gas turbine combustion chamber according to Claim 3, wherein the outlet openings of the radial air flow passages (22) are formed on a radially outer portion of the axial surface (18) of the flame tube cover (17).
5 The gas turbine combustion chamber according to any one of the Claims 1 to 4, wherein the radial air flow passages (22) extend between the radially inner inlet openings (24) and the radially outer outlet openings within the flame tube cover (17).
6. The gas turbine combustion chamber according to any one of the Claims 1 to 5, wherein the radial air flow passages (22) between the radially inner inlet openings (24) and the radially outer outlet openings are closed.
/. The gas turbine combustion chamber according to any one of the Claims 1 to 6, wherein the radial air flow passages (22) between the radially inner inlet openings (24) and the radially outer outlet openings follow a curved or spiral course.
8. The gas turbine combustion chamber according to any one of the Claims 1 to 7, wherein the burner (12) comprises an inlet ring (26) via which air enters the air axial air flow passage (20) formed between the mixing tube (19) of the burner (12) and the flame tube cover (17).
9. The gas turbine combustion chamber according to Claim 8, wherein the inlet ring (26) has radial openings (27) via which the air enters the axial air flow passage (20) in the radial direction.
10. The gas turbine combustion chamber according to any one of the Claims 1 to 9, wherein a seal (28) is positioned on a downward end of the axial air flow passage (20) between the mixing tube (19) and the flame tube cover (17).
11. The gas turbine combustion chamber according to any one of the Claims 1 to 10, wherein the flame tube cover (17) is produced by way of a generative manufacturing method, namely via 3D printing.