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Air fairing and nozzle of gas turbine

A technology of air rectification and gas turbine, which is applied in the direction of combustion chamber, combustion method, combustion equipment, etc., can solve the problems that cannot solve the problem of inhomogeneity of incoming air and extra air pressure loss, and achieve optimal structural design, reduce pressure loss, increase ventilation The effect of flow area

Pending Publication Date: 2021-07-09
CHINA UNITED GAS TURBINE TECH CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The combustion chamber cover in this patent can improve the cooling efficiency by setting the impingement guide cooling pipe at the air inlet of the casing, but it cannot solve the inhomogeneity of the incoming air upstream of the nozzle swirler and the extra air brought by the fairing. pressure loss problem

Method used

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  • Air fairing and nozzle of gas turbine
  • Air fairing and nozzle of gas turbine
  • Air fairing and nozzle of gas turbine

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0036] like figure 1 As shown, the air fairing 5 of the gas turbine includes the front end plate 1 of the fairing and the outer wall 2 of the fairing. The front end plate 1 of the fairing is circular, and its outer edge is connected with the outer wall 2 of the fairing. The front end plate 1 of the fairing is provided with several first rectifying holes 11, and the first rectifying holes 11 are annularly arranged on the front end plate 1 of the fairing; There are several second rectifying holes 21 , and the second rectifying holes 21 are arranged along the circumferential direction of the outer wall 2 of the fairing.

[0037] At least one deflector 3 is arranged on the inner side of the fairing outer wall 2 (taking two deflectors as an example, the deflector 3 includes a first deflector 31 and a second deflector 32), and the deflector 3 is along the The central axis of the fairing outer wall 2 is a ring structure arranged symmetrically, and the deflector 3 is connected with ...

Embodiment 2

[0040] like figure 1 As shown, the air fairing 5 of the gas turbine includes the front end plate 1 of the fairing and the outer wall 2 of the fairing. The front end plate 1 of the fairing is circular, and its outer edge is connected with the outer wall 2 of the fairing. The front end plate 1 of the fairing is provided with several first rectification holes 11, preferably, the first rectification holes 11 are evenly distributed in the circumferential direction of the front end plate 1 of the fairing, so that the airflow flowing through the front end plate 1 of the fairing is more uniform . The fairing outer wall 2 is provided with a first area 20, the first area 20 is the area close to the front end plate 1 of the fairing, and several second rectifying holes 21 are provided in the first area 20, preferably, the second rectifying holes 21 are arranged along the rectifying The circumferential direction of the cowl outer wall 2 is evenly arranged, so that the airflow flowing thr...

Embodiment 3

[0044] like figure 1 As shown, the air fairing 5 of the gas turbine includes the front end plate 1 of the fairing and the outer wall 2 of the fairing. The front end plate 1 of the fairing is circular, and its outer edge is connected with the outer wall 2 of the fairing. The front end plate 1 of the fairing is provided with several first rectifying holes 11, and the first rectifying holes 11 are annularly arranged on the front end plate 1 of the fairing; There are several second rectifying holes 21 , and the second rectifying holes 21 are arranged along the circumferential direction of the outer wall 2 of the fairing.

[0045] In an embodiment of the application, the shape of the first rectification hole 11 and the second rectification hole 21 can be a combination of one or more of round holes, oblong holes, and drop-shaped holes. The first rectification hole 11 and the second rectification hole The shapes of the two rectification holes 21 are not limited to the above types, ...

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Abstract

The invention discloses an air fairing and a nozzle of a gas turbine. The air fairing comprises a fairing front end plate, a fairing outer wall and N flow guide plates arranged on the inner side of the fairing outer wall, wherein N is a positive integer larger than or equal to 1, the fairing front end plate is connected with the fairing outer wall, and a plurality of first flow rectifying holes are formed in the fairing front end plate; a plurality of second flow rectifying holes are formed in a first area of the fairing outer wall; the first end of at least one flow guide plate is connected with the inner side of the fairing outer wall; and a part of air enters the air fairing through the flow rectifying holes of the fairing front end plate in the axial direction, the other part of air enters the air fairing through the flow rectifying holes of the fairing outer wall in the circumferential direction, and under the action of at least one flow guide plate, the air entering the air fairing flows in the axial direction and flows out of the other end of the air fairing. According to the air fairing and the nozzle structure, the uniformity of incoming flow air on the upstream of a cyclone is improved, and the pressure loss of the air fairing is reduced.

Description

technical field [0001] The present application relates to the field of gas turbines, in particular to an air fairing and a nozzle of a gas turbine. Background technique [0002] The gas turbine combustor head has a plurality of nozzles, a central nozzle is arranged at the central axis, and several peripheral nozzles are arranged around it. The fairing is a part of the nozzle air flow path, located upstream of the nozzle swirler, and its main purpose is to rectify the airflow to ensure a uniform incoming air for the swirler. [0003] Patent CN204513463U discloses a combustion chamber cap structure with an impingement diversion cooling pipe, and the shell of the cap is respectively provided with a front baffle, a rear baffle and a plurality of air inlets. Each air inlet inside the shell is provided with an impingement diversion cooling pipe, which can guide the cooling gas to the expansion section of the on-duty nozzle that is more heated, thereby prolonging the stay of the c...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F23R3/16F23R3/26F23R3/12
CPCF23R3/16F23R3/26F23R3/12
Inventor 赵光军崔玉峰王昆
Owner CHINA UNITED GAS TURBINE TECH CO LTD