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Nozzle for a gas turbine combustor

A technology for gas turbines and burners, applied in the directions of burners, combustion chambers, combustion methods, etc., can solve problems such as reduced reliability, increased space requirements, and increased manufacturing costs

Inactive Publication Date: 2016-11-09
GENERAL ELECTRIC TECH GMBH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This measure leads to additional pressure losses, increased manufacturing costs and increased space requirements, together with reduced reliability of the fuel injection system and its associated increased commissioning and maintenance costs

Method used

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  • Nozzle for a gas turbine combustor
  • Nozzle for a gas turbine combustor

Examples

Experimental program
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Embodiment Construction

[0037] figure 1 The nozzle 1 in an incinerator 8 for a gas turbine according to the present invention is shown. The nozzle includes at least one inner channel 3 (inner axial inlet channel), wherein at least one vortex channel 4 (outer vortex channel) extends around the outer diameter of the inner channel 3. The inner passage 3 and the vortex passage 4 extend from the nozzle inlet 20 to the mixing zone 5 downstream of the inner passage 3 and the vortex passage 4. The mixing zone 5 is a cylindrical hole passing through the nozzle, wherein the axis 16 of the cylindrical hole of the mixing zone is perpendicular to the axis 18 of the nozzle (see also figure 2 ).

[0038] The outlet channel 6 is arranged at the other side of the mixing zone and the inner channel 3 and the vortex channel 4 (downstream of the mixing zone 5), wherein the outlet channel 6 extends from the mixing zone 5 to the outlet 22 of the nozzle.

[0039] The shielding fluid hole 10 (shielding fluid passage) is provide...

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PUM

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Abstract

The invention relates to a nozzle (1) for a gas turbine combustor, and it comprises an inner passage (3), a vortex passage (4), a mixing zone (5) and an outlet passage (6), wherein the nozzle (1) ) extends from the inlet (20) to the outlet (22), the vortex channel (4) is arranged around the inner channel (3), the inner channel (3) and the vortex channel (4) extending from the inlet (20) The mixing zone (5) extends from the inner passage (3) and the vortex passage (4) to the outlet passage (6), and the outlet passage (6) extends from the mixing zone (5) to the outlet (22). Also described is a burner (8) comprising a nozzle (1) and a gas turbine, together with a method of using a nozzle (1).

Description

Technical field [0001] The present disclosure relates to a nozzle for a gas turbine combustor, and more particularly to a nozzle for a gas turbine combustor having a swirl passage and an inner passage. Background technique [0002] Most of the current nozzle systems used in gas turbine combustors are designed as ordinary jet or swirl nozzles. The main differences between these nozzle types are atomization quality, spray cone angle and pressure drop. The vortex nozzle provides good atomization combined with a large spray cone angle. In contrast, ordinary jets provide lower fuel pressure drop, but also provide poor atomization quality and a smaller spray cone angle. [0003] The ordinary jet nozzle is composed of axially-opened holes, and the corresponding manufacturing cost is low. Ordinary jet nozzles also require less space in the combustor compared to swirl nozzles. The swirl nozzle generally has a geometrically complex swirler combined with a precision nozzle outlet shape, a...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F23R3/38
CPCF23R3/38F23D11/383
Inventor M.扎贾达茨D.A.彭内尔T.C.默茨库斯
Owner GENERAL ELECTRIC TECH GMBH