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Burner assembly

a technology of burners and components, applied in the direction of burners, hot gas positive displacement engine plants, combustion processes, etc., can solve the problems of small drop formation and less effective penetration, and achieve the effect of narrowing the radial fuel profil

Inactive Publication Date: 2013-05-02
SIEMENS AG
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  • Summary
  • Abstract
  • Description
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  • Application Information

AI Technical Summary

Benefits of technology

This patent discusses the use of full jet nozzles in fuel nozzles for gas turbines. These nozzles have several advantages, including the ability to change the fuel distribution without causing turbulence. They also produce a full jet, which allows for better penetration depth compared to pressure swirl nozzles. However, to achieve higher penetration depth with pressure swirl nozzles, a much higher pressure is required, which can be expensive. The full jet nozzle can be a hole running in the attachment, and can be arranged along a helical peripheral line to enhance fuel concentration. This helps to improve the mixing of fuel and air between the pilot burner and the main burner. Overall, the use of full jet nozzles can improve engine performance more efficiently while keeping costs low.

Problems solved by technology

With pressure swirl nozzles a higher preliminary pressure causes smaller drops to form, which in turn penetrate less effectively.

Method used

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Embodiment Construction

[0088]FIG. 1 shows a detail of an inventive burner assembly in the region of a main burner 107. Swirl blades 17 are arranged around the lance in the housing 12 of the main burner 107. The swirl blades 17 are arranged along the periphery of the lance in the housing 12. The swirl blades 17 direct a compressor air flow 15 into the part of the burner 107 leading to a combustor. The air is made to swirl by the swirl blades 17. The lance also comprises a fuel channel 16. The burner 107 further comprises an attachment 13 on the side leading to a combustor. The attachment 13 can be welded or screwed to the lance for example. The fuel nozzles are preferably arranged downstream of the swirl blades 17 in the attachment 13 and are thus connected for flow purposes to the fuel channel 16, shown here as an oil channel. The inventive burner assembly preferably comprises eight such main burners 107 arranged in a circle (see FIG. 12). The main burners 107 here are arranged around a pilot burner (see ...

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PUM

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Abstract

A burner assembly for a gas turbine is provided. The burner assembly has a combustor, a centrally arranged pilot burner and plurality of main burners surrounding the pilot burner. Each main burner has a cylindrical housing having a lance which is centrally arranged therein and has a fuel channel for liquid fuel. The lance is supported on the housing by swirl blades and an attachment is arranged on the lance in the direction of the combustor. The liquid fuel nozzle is arranged in the attachment downstream of the swirl blades and connected to the fuel channel. For the improved mixing of the fuel with the air, the liquid fuel nozzle is designed as a full jet nozzle and the full jet nozzle has a length and a diameter, the ratio of the length to the diameter is at least 1.5.

Description

CROSS REFERENCE TO RELATED APPLICATIONS[0001]This application is the US National Stage of International Application No. PCT / EP2011 / 061101 filed Jul. 1, 2011 and claims the benefit thereof. The International Application claims the benefits of European application No. 10168107.0 filed Jul. 1, 2010, both of the applications are incorporated by reference herein in their entirety.FIELD OF THE INVENTION[0002]The present invention relates to a burner assembly for a gas turbine having at least one combustor, wherein the burner assembly comprises a centrally arranged pilot burner and a number of main burners surrounding the pilot burner, wherein each of the main burners comprises a cylindrical housing having a lance which is centrally arranged therein and has a fuel channel for liquid fuel, wherein the lance is supported on the housing by means of swirl blades and an attachment is arranged on the lance in the direction of the combustor, wherein at least one liquid fuel nozzle is arranged in ...

Claims

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Application Information

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IPC IPC(8): F23R3/34
CPCF23C2900/07021F23R3/343F23R3/286F23D11/38
Inventor BODE, SIEGFRIEDFOX, TIMOTHY A.GRIEB, THOMASHASE, MATTHIASMEISL, JURGENPFADLER, SEBASTIAN
Owner SIEMENS AG
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