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Nozzle rod part, fuel nozzle and aero-engine gas turbine

A nozzle rod and fuel technology, applied in the combustion chamber, combustion method, combustion equipment and other directions, can solve the problems of low fuel nozzle life and easy coking of fuel

Active Publication Date: 2015-06-17
AECC COMML AIRCRAFT ENGINE CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0008] One of the objectives of the present invention is to provide a nozzle stem, a fuel nozzle and an aero-engine gas turbine, which solves the problem that the fuel in the nozzle stem is easy to coke under various working conditions in the prior art, and the problem that the life of the fuel nozzle is low

Method used

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  • Nozzle rod part, fuel nozzle and aero-engine gas turbine
  • Nozzle rod part, fuel nozzle and aero-engine gas turbine
  • Nozzle rod part, fuel nozzle and aero-engine gas turbine

Examples

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Embodiment 1

[0053] see figure 1 , figure 2 , Figure 3a , Figure 3b and Figure 3c , Embodiment 1 of the present invention provides a nozzle rod 12 , the nozzle rod 12 includes a rod-shaped body and a main oil passage 34 and an auxiliary oil passage 35 arranged on the rod-shaped body. Wherein: the auxiliary oil passage 35 is arranged around the main oil passage 34 , and the fluid in the main oil passage 34 and the fluid in the auxiliary oil passage 35 can exchange heat through the medium between the auxiliary oil passage 35 and the main oil passage 34 . The fluid that enters through the inlet of the main oil passage 34 can flow out through the outlet of the main oil passage 34; The position of the outlet port of the oil passage 34 turns back to the position close to the position of the inlet port of the main oil passage 34 , and then flows out through the oil outlet port of the auxiliary oil passage 35 .

[0054] see figure 2 , the heat insulation cavity 511 is filled with low th...

Embodiment 2

[0073] see Figure 4 , Figure 5 and Figure 6 The technical solutions of this embodiment and the above embodiments have the following differences: the number of hollow passages included in the auxiliary oil passage 135 is different, and the specific realization of the grooves forming the hollow passages is different. In this embodiment, the auxiliary oil passage 135 includes two hollow passages that are not connected to each other. The structures of the hollow passages may be the same or different, and the same is used as an example here. The grooves of each hollow passage include three linear grooves 130 , 131 , 132 , the linear grooves 130 and 131 are connected through a connecting section 150 , and the linear grooves 131 and 132 are connected through a connecting section 151 . The communication sections 150 and 151 may be circumferential, or have a certain angle with the axial direction, and the like. Preferably, both the communication sections 150, 151 are circumferent...

Embodiment 3

[0085] This embodiment has the following differences from the technical solutions of the above two embodiments. The hollow channel is formed in a different way. In this embodiment, the hollow channel is jointly formed by a groove provided on the inner wall of the fuel casing and the outer wall of the central pipeline, and the outer wall of the central pipeline is a smooth outer wall.

[0086] In this embodiment, the groove forming the hollow channel may also adopt the implementation methods in the above-mentioned embodiments, such as a spiral groove or a linear groove. Similarly, the number of spiral grooves and whether the spiral grooves are directly connected or connected through a transition part can refer to the content described above. The number of linear grooves and whether the linear grooves are directly connected or connected through transition parts can also refer to the content described above, and will not be repeated here.

[0087] Compared with the prior art, th...

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Abstract

The invention discloses a nozzle rod part, a fuel nozzle and an aero-engine gas turbine, relates to the technical field of aero-engines, and is used for solving the problems of easy coking of fuel of the nozzle rod part and short service life of the fuel nozzle in a working state in a fuel supply scheme of using a main fuel way as a discontinuous working fuel way and using a secondary fuel way as a continuous working fuel way in the prior art. The nozzle rod part comprises a rod body, a main fuel way and a secondary fuel way. The secondary fuel way is arranged at the periphery of the main fuel way; a fluid in the main fuel way and a fluid in the secondary fuel way can exchange heat; the fluid entering from a fluid inlet of the main fuel way can flow out through a fluid outlet of the main fuel way; and the fluid entering from a fuel inlet of the secondary fuel way can at least experience once of the process of returning to a position near the fluid inlet of the main fuel way from a position near the fluid outlet of the main fuel way in the secondary fuel way, and then flows out by the fuel outlet of the secondary fuel way. The nozzle rod part can prevent the fuel coking problem, and can prolong the service life of the fuel nozzle.

Description

technical field [0001] The invention relates to the technical field of aero-engines, in particular to a nozzle rod, a fuel nozzle and an aero-engine gas turbine. Background technique [0002] As we all know, the function of the gas turbine fuel nozzle is to deliver high-pressure fuel from the fuel manifold to the combustor casing for combustion. Typically, a fuel nozzle includes a nozzle inlet near the fuel rail, one or more fuel passages, a nozzle outlet connected to a swirler, a nozzle mount, a nozzle stem connected to the nozzle mount, and a nozzle stem that is approximately perpendicular to the nozzle stem. nozzle head. The nozzle head is fixed with the nozzle stem, and the nozzle mount is used to fix the nozzle stem on the combustion chamber casing. [0003] Most fuel injectors include multiple fuel circuits for better flow regulation. For example, the fuel oil circuit can be divided into a main oil circuit with a large fuel flow and an auxiliary oil circuit with a s...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F23R3/28
Inventor 陈毓卿陈苏涛
Owner AECC COMML AIRCRAFT ENGINE CO LTD
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