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CN-116951468-B - Gas turbine and nozzle thereof

CN116951468BCN 116951468 BCN116951468 BCN 116951468BCN-116951468-B

Abstract

The application discloses a gas turbine and a nozzle thereof, and relates to the technical field of nozzles. The nozzle comprises an end cover, a first fuel spray rod arranged on the end cover, a plurality of first spray holes and a plurality of second fuel spray rods arranged on the end cover, wherein the first fuel spray rod comprises a first flow channel and a second flow channel, the tail end of the first fuel spray rod is provided with a plurality of first spray holes, each first spray hole is communicated with the first flow channel, and the second fuel spray rods are uniformly distributed around the first fuel spray rod. According to the application, through the arrangement of the first fuel spray rod and the second fuel spray rod, the fuel sprayed from the first fuel spray rod is subjected to diffusion combustion, and the fuel sprayed from the second fuel spray rod is subjected to premixed combustion, so that flowing air can only disturb the flame of diffusion combustion but cannot disturb the flame of premixed combustion in the whole combustion process, and further the phenomena of difficult ignition or unstable combustion when the gas turbine is started or is in a low working condition can be effectively avoided.

Inventors

  • MOU YING
  • LI MING
  • LI XIAOMENG
  • JIANG JIAHUA

Assignees

  • 中国航发燃气轮机有限公司

Dates

Publication Date
20260505
Application Date
20230907

Claims (8)

  1. 1. A nozzle, comprising: An end cap (1); The first fuel spray rod (4) is arranged on the end cover (1), the first fuel spray rod (4) comprises a first flow channel (46) and a second flow channel (45), a plurality of first spray holes (49) are formed in the tail end of the first fuel spray rod (4), and each first spray hole (49) is communicated with the first flow channel (46); The second fuel spray bars (3) are arranged on the end cover (1), the second fuel spray bars (3) are uniformly distributed around the first fuel spray bars (4), a plurality of second spray holes (31) are formed in each second fuel spray bar (3), and the length of each second fuel spray bar (3) is smaller than that of the first fuel spray bar (4); A first feed pipe (7) arranged on the end cover (1), wherein the first feed pipe (7) is communicated with the first flow channel (46), and the first feed pipe (7) is communicated with each second fuel spray rod (3); The first fuel spray rod (4) further comprises a third flow passage (44), the tail end of the first fuel spray rod (4) is further provided with a plurality of third spray holes (48), and each third spray hole (48) is communicated with the third flow passage (44), the end cover (1) is further provided with a second feeding pipe (6), and the second feeding pipe (6) is communicated with the third flow passage (44); The tail end of the first fuel spray rod (4) further comprises a rotational flow fan blade (8), and the rotational flow fan blade (8) is used for enabling air in the second flow channel (45) to form rotational flow.
  2. 2. The nozzle according to claim 1, wherein an included angle formed by an axis of each third nozzle hole (48) and an axis of the first fuel boom (4) ranges from 20 ° to 60 °.
  3. 3. The nozzle according to claim 1 or 2, further comprising: the fuel injection device comprises a plurality of third fuel injection bars (2) arranged on an end cover (1), wherein each third fuel injection bar (2) is uniformly distributed around a first fuel injection bar (4), and the length of each third fuel injection bar (2) is smaller than that of the first fuel injection bar (4), and a plurality of fourth spray holes (21) are formed in each third fuel injection bar (2); and the third feeding pipes (5) are arranged on the end covers (1), and the third feeding pipes (5) are communicated with the third fuel spray bars (2).
  4. 4. A nozzle according to claim 3, characterized in that each third fuel boom (2) is located at a greater distance from the first fuel boom (4) than each second fuel boom (3) is located at the first fuel boom (4) in the radial direction of the first fuel boom (4).
  5. 5. A nozzle according to claim 3, characterized in that the axis of each second nozzle hole (31) is perpendicular to the axis of the first fuel boom (4), and the axis of each fourth nozzle hole (21) is perpendicular to the axis of the first fuel boom (4).
  6. 6. A nozzle according to claim 3, wherein the first fuel stem (4) comprises a first fuel pipe (41), a second fuel pipe (42) and a third fuel pipe (43) which are sequentially sleeved from outside to inside, the first flow passage (46) is formed in the third fuel pipe (43), the second flow passage (45) is formed between the second fuel pipe (42) and the third fuel pipe (43), and the third flow passage (44) is formed between the first fuel pipe (41) and the second fuel pipe (42).
  7. 7. Nozzle according to claim 6, characterized in that the first fuel pipe (41) comprises an air inlet gap (47), which air inlet gap (47) is intended for air inside the combustion chamber (9) to enter the second flow channel (45).
  8. 8. A gas turbine comprising a nozzle as claimed in any one of claims 1 to 7.

Description

Gas turbine and nozzle thereof Technical Field The application relates to the technical field of nozzles, in particular to a gas turbine and a nozzle thereof. Background The gas turbine is a heat engine which takes continuously flowing gas as working medium to drive the turbine to rotate at high speed and convert fuel heat energy into mechanical work. At present, with the continuous increase of environmental awareness, whether pollutant emission indexes are qualified or not becomes an admittance condition for the gas turbine to enter the market. In order to reduce emissions of pollutants such as Nitrogen Oxides (NOX), a lean-burn technique is often used in gas turbines that have been the main stream. Lean combustion, in turn, refers to clean combustion techniques in which the fuel in the mixture is less than normal stoichiometric, which can effectively reduce emissions of nitrogen oxides, hydrocarbons, and carbon monoxide. Because of the low fuel content of the mixture in lean combustion, the flame of lean combustion is extremely sensitive to flow disturbances, and when the gas turbine is started or in low operating conditions, it is often difficult to ignite and perform stable combustion. Disclosure of Invention The application aims to provide a gas turbine and a nozzle thereof, which are used for solving the technical problems of lean oil premixed combustion and unstable combustion of the gas turbine in the prior art. In order to achieve the above purpose, the present application provides the following technical solutions: in a first aspect, the application provides a nozzle, which comprises an end cover, first fuel spray bars arranged on the end cover, first flow channels and second flow channels arranged in the first fuel spray bars, a plurality of first spray holes arranged at the tail end of the first fuel spray bars and communicated with the first flow channels, a plurality of second fuel spray bars arranged on the end cover and uniformly distributed around the first fuel spray bars, a plurality of second spray holes arranged on each second fuel spray bar, a first feed pipe arranged on the end cover and communicated with the first flow channels, and a second feed pipe communicated with each second fuel spray bar, wherein the length of each second fuel spray bar is smaller than that of the first fuel spray bar. As one implementation mode of the embodiment of the application, a third flow channel is further arranged in the first fuel spray rod, a plurality of third spray holes are further arranged at the tail end of the first fuel spray rod, each third spray hole is communicated with the third flow channel, a second feeding pipe is further arranged on the end cover, and the second feeding pipe is communicated with the third flow channel. As one implementation mode of the embodiment of the application, the range of an included angle formed by the axial lead of each third spray hole and the axial lead of the first fuel spray rod is more than or equal to 20 degrees and less than or equal to 60 degrees. The embodiment of the application further comprises a plurality of third fuel spray bars arranged on the end cover, wherein each third fuel spray bar is uniformly distributed around the first fuel spray bar, the length of each third fuel spray bar is smaller than that of the first fuel spray bar, a plurality of fourth spray holes are formed in each third fuel spray bar, each fourth spray hole is uniformly distributed around the axial lead of the corresponding third fuel spray bar, and a third feed pipe arranged on the end cover is communicated with each third fuel spray bar. As one implementation of the embodiment of the present application, a distance from each third fuel boom to the first fuel boom is greater than a distance from each second fuel boom to the first fuel boom in a radial direction of the first fuel boom. As an implementation manner of the embodiment of the present application, the end of the first fuel spray rod further includes a swirl fan blade, where the swirl fan blade is used to make air in the second flow channel form a swirl. As one implementation mode of the embodiment of the application, the axial lead of each second spray hole is perpendicular to the axial lead of the first fuel spray rod, and the axial lead of each fourth spray hole is perpendicular to the axial lead of the first fuel spray rod. As one implementation mode of the embodiment of the application, the first fuel spray rod comprises a first fuel pipe, a second fuel pipe and a third fuel pipe which are sleeved in sequence from outside to inside, the first flow channel is formed in the third fuel pipe, the second flow channel is formed between the second fuel pipe and the third fuel pipe, and the third flow channel is formed between the first fuel pipe and the second fuel pipe. As an implementation manner of the embodiment of the present application, the first fuel pipe includes an air inlet notch, and the air inlet notc