CN-119802679-B - Combustion chamber and pure hydrogen gas turbine with same

Abstract

The invention relates to the technical field of gas turbines, in particular to a combustion chamber and a pure hydrogen gas turbine with the combustion chamber. The combustion chamber comprises at least one group of nozzle assemblies, wherein each nozzle assembly comprises a fuel runner, a combustion-supporting gas runner and a combustion-supporting gas runner, wherein the fuel runner comprises a runner body and a nozzle body which are sequentially arranged, an arc-shaped transition section is arranged between the runner body and the nozzle body, the inner side wall of the outlet end of the nozzle body is obliquely arranged to form an outflow angle so that fuel gas forms axial vortex at the outlet of the nozzle body, and the combustion-supporting gas runner is sleeved and installed on the outer side of the fuel runner. Under the action of the air serving as the combustion-supporting gas by utilizing the guide sharp angle to match with the inner wall of the combustion-supporting gas flow passage and the air serving as the combustion-supporting gas at the periphery, the hydrogen serving as the fuel gas generates axial vortex at the nozzle body, the axial vortex develops towards the downstream of the nozzle body, the speed distribution of the axial vortex does not generate reverse axial speed, and the formation of a backflow area is avoided, so that the risk of backfire of hydrogen flame is reduced, and the generation of nitrogen oxides is reduced.

Inventors

• YANG YANG
• LUO ANDONG
• YU GUANGYUAN
• HUANG QUN
• XIANG JIEQIONG

Assignees

• 无锡华天燃气轮机有限公司
• 无锡华天航空动力有限公司

Dates

Publication Date

20260508

Application Date

20250227

Claims (8)

1. 1. A combustion chamber comprising at least one set of nozzle assemblies, the nozzle assemblies comprising: The fuel runner (1) comprises a runner body (101) and a nozzle body (103) which are sequentially arranged, an arc-shaped transition section (102) is arranged between the runner body (101) and the nozzle body (103), the inner side wall of the outlet end of the nozzle body (103) is obliquely arranged away from the axis of the runner body to form an outflow angle, and the outlet end of the nozzle body (103) is formed with at least one pair of guide sharp angles (1031) so that fuel gas forms at least one axial vortex at the outlet of the nozzle body (103); The combustion-supporting gas flow passage (2) is sleeved and arranged at the outer side of the fuel flow passage (1); Three pairs of guide sharp corners (1031) are arranged at intervals, the three pairs of guide sharp corners (1031) are uniformly arranged around the circumference of the fuel runner (1), the inner side edge of the nozzle body (103) between the same pairs of guide sharp corners (1031) is a straight edge (1032), and the inner side edge of the nozzle body (103) between two adjacent guide sharp corners (1031) of different pairs of guide sharp corners (1031) is a concave edge (1033).
2. 2. The combustor of claim 1, wherein a plurality of groups of said nozzle assemblies are arranged at intervals to form nozzle clusters, a plurality of said nozzle clusters being arranged at intervals in a circumferential direction, a plurality of said nozzle clusters being arranged in rotational symmetry.
3. 3. A combustion chamber according to claim 2, wherein two rows of said nozzle assemblies are radially arranged in the same nozzle cluster, one of the straight edges (1032) on the nozzle assembly arranged at the periphery being arranged towards the rotational symmetry axis between a plurality of said nozzle clusters, and one of the straight edges (1032) on the nozzle assembly arranged at the inner side being arranged away from the rotational symmetry axis between a plurality of said nozzle clusters.
4. 4. A combustion chamber according to claim 3, wherein the nozzle clusters are arranged in a fan shape, and the central angle of one of the nozzle clusters is 50 ° -70 °.
5. 5. The combustion chamber according to claim 1, characterized in that the width of the straight edge (1032) is not greater than the width of the concave edge (1033).
6. 6. The combustor of claim 1, wherein a plurality of said nozzle assemblies are arranged in an annular configuration.
7. 7. The combustion chamber according to claim 1, characterized in that inside the guiding tip (1031) there is provided a rounded corner.
8. 8. A pure hydrogen gas turbine having a combustion chamber according to any one of claims 1 to 7.

Description

Combustion chamber and pure hydrogen gas turbine with same Technical Field The invention relates to the technical field of gas turbines, in particular to a combustion chamber and a pure hydrogen gas turbine with the combustion chamber. Background The gas turbine is used as a high-efficiency power device and has wide application in the fields of power generation, aviation and industry. As global energy structures are transformed to low carbonization, hydrogen energy is an important choice for replacing fossil fuels due to its zero carbon emission characteristics. However, the conventional combustion chamber of the gas turbine is mainly designed for hydrocarbon fuels such as natural gas, and the pure hydrogen is directly used as the fuel to face a plurality of challenges, so that development of a novel combustion technology adapting to the hydrogen fuel characteristic is needed to meet the environmental protection requirement. The existing pure hydrogen fuel combustion chamber mostly adopts a micro-mixed combustion technology, and flashback is restrained by reducing the diameter of a fuel nozzle and improving the mixing speed. However, the micro-mixing structure requires a large number of micro-nozzles, which results in complex processing and high cost, and the diffusion combustion mode is easy to damage when the flow rate of the single-hole fuel is increased, and part of the design also introduces a rotational flow device to enhance mixing, but a backflow area generated by rotational flow can aggravate the backfire risk of hydrogen flame, and the micro-mixing structure has complex structure and high pressure loss, and is difficult to adapt to the requirements of high diffusivity and low turbulence of the hydrogen fuel. Therefore, the axial vortex mixing technology is considered, not only can backflow be avoided, but also the structure is simple to realize, so that the contradictory requirements in hydrogen combustion can be effectively balanced according to the hydrogen fuel combustion chamber structure in the prior art, namely, on one hand, the rapid mixing of hydrogen and air is realized to reduce the generation of local high temperature and NO x, on the other hand, the backflow area or high turbulence is avoided in the mixing process, and flame tempering and thermoacoustic oscillation are prevented. Disclosure of Invention In view of the above, the present invention provides a combustor and a pure hydrogen gas turbine with the same, so as to solve the problem that the structure of the hydrogen fuel combustor in the prior art cannot avoid the generation of a backflow area or high turbulence during rapid mixing. In a first aspect, the present invention provides a combustion chamber comprising at least one set of nozzle assemblies, the nozzle assemblies comprising: the fuel runner comprises a runner body and a nozzle body which are sequentially arranged, an arc-shaped transition section is arranged between the runner body and the nozzle body, the inner side wall of the outlet end of the nozzle body is obliquely arranged away from the axis of the runner body to form an outflow angle, and the outlet end of the nozzle body is formed with at least one pair of guide sharp angles, so that fuel gas forms at least one axial vortex at the outlet of the nozzle body; The combustion-supporting gas flow passage is sleeved and arranged on the outer side of the fuel flow passage. When the combustion chamber works, fuel gas is sprayed out from the fuel flow channel, combustion-supporting gas is sprayed out from the combustion-supporting gas flow channel, and when the fuel gas is in the position of the flowing nozzle body, axial vortex is formed under the action of the guide sharp angle and the inner side wall of the nozzle body, and then the fuel gas is mixed with the combustion-supporting gas in the peripheral combustion-supporting gas flow channel. When the combustion chamber is applied to a pure hydrogen gas turbine, hydrogen is used as fuel gas, the maximum laminar flame speed in air is 8 times that of methane flame during hydrogen combustion, so that the hydrogen flame is easy to temper, and the hydrogen used as fuel gas is enabled to generate axial vortex at the nozzle body under the action of the air used as combustion supporting gas by utilizing the guide sharp angle to match with the inner wall and the periphery of the combustion supporting gas flow passage, so that the hydrogen and the air are fully mixed. The axial vortex develops downstream of the nozzle, the velocity distribution of the axial vortex does not generate reverse axial velocity, and the formation of a backflow zone is avoided, so that the risk of backfire of the hydrogen flame is reduced, and the generation of nitrogen oxides is reduced. In an alternative embodiment, the guide sharp angles are arranged in a plurality of pairs, the inner side edge of the nozzle body between the same pair of guide sharp angles is a straight edge, and the inner side ed