Unlock instant, AI-driven research and patent intelligence for your innovation.

Gas Turbine Combustor

A technology for gas turbines and burners, which is applied in the direction of combustion chambers, combustion methods, and combustion equipment, and can solve problems such as shortened fuel nozzle distances, narrow fuel nozzle spaces, and thinner fuel nozzle outer diameters, and achieve high structural reliability. Effect

Active Publication Date: 2021-10-08
MITSUBISHI HEAVY IND LTD
View PDF7 Cites 0 Cited by
  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0008]However, in a gas turbine combustor composed of a plurality of fuel nozzles and a fuel nozzle plate structurally supporting the fuel nozzles, if the As the number of fuel nozzles increases, the distance between fuel nozzles becomes shorter
[0009] Therefore, since the space around the fuel nozzle is narrow, in order to secure a space for joining the fuel nozzle and the fuel nozzle plate, the fuel nozzle as a flow path of air The space between the fuel nozzles needs to be reduced with the increase in the number of nozzles

Method used

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
View more

Image

Smart Image Click on the blue labels to locate them in the text.
Viewing Examples
Smart Image
  • Gas Turbine Combustor
  • Gas Turbine Combustor
  • Gas Turbine Combustor

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0031] First, use figure 1 An example of the constituent elements of the gas turbine device 1 will be described.

[0032] like figure 1As shown, the gas turbine device 1 consists of the following portion: The compressor 3 is taken into air 2 from the atmosphere; the combustor 7, which combuses the compressed air 4 and fuel 5 compressed in the compressor 3, form High temperature and high pressure combustion gas 6; gas turbine 8, which is driven by the combustion gas 6 generated by the burner 7, and the energy of the combustion gas 6 is taken out as a rotational force; and the generator 9, which uses the rotational power of the gas turbine 8 to power generation.

[0033] The burner 7 is composed of an end flange 10, an outer cylinder 11, an air orifice plate 12, a fuel nozzle plate 13, a fuel nozzle 14, and a liner 15, compressed by the compressed air 4 and the lining 15 by the outer cylinder 11 The flow path 16 flows into the burner 17. However, a part of the compressed air 4 is fl...

Embodiment 2

[0055] Figure 5 The structure of the combustion nozzle 17 in Example 2 of the gas turbine burner of the present invention is shown. This picture is not Figure 4 Under the state of the air orifice plate, 41 downstream 41 (see Figure 4 The fuel nozzle plate 13 and the fuel nozzle 14 are observed.

[0056] Figure 5 The combustion nozzle 17 of the combustor 7 of the present embodiment is usually having a plurality of fuel supply systems. Figure 5 In the case where the outer diameter of the fuel nozzle 14 of the fuel nozzle 14 is located is located in the central portion of the combustion nozzle 17 to surround the center-side fuel nozzle group 50 of the combustion mouth, there is a plurality of burning nozzles outer peripheral fuel. The nozzle group 51, the outer peripheral side fuel nozzle group 51 having different outer diameters, and the outer peripheral fuel nozzle group 51 of the combustion mouth is opposite to the center side fuel nozzle group 50 of the combustion mouth. The ou...

Embodiment 3

[0063] Figure 7 The structure of the combustion nozzle 17 in Example 3 of the gas turbine burner of the present invention is shown.

[0064] Drawing Figure 5 The same, it is not Figure 4 Under the state of the air orifice plate, 41 downstream 41 (see Figure 4 The fuel nozzle plate 13 and the fuel nozzle 14 are observed.

[0065] exist Figure 7 In the center side fuel nozzle group 50 disposed in the central combustion nozzle disposed in the central combustion nozzle 17 and the outer peripheral side fuel nozzle group 51 disposed in the outer circumference of the combustion nozzle 17, the fuel supply system is different. The larger the fluid force acting on the fuel nozzle 14, the larger the outer peripheral side of the combustion nozzle 17, so that the fluid force acting on the outer peripheral fuel nozzle group 51 of the combustion mouth is 50.

[0066] Therefore, in the present embodiment, in the peripheral side fuel nozzle group 51 in a plurality of burner outer peripheral fuel ...

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More

PUM

No PUM Login to View More

Abstract

The present invention provides a gas turbine combustor with structural reliability to the vibration under the fluid force and high environmental performance owing to the uniform combustion, which are achieved by optimizing the outer diameter of the fuel nozzle under the fluid force that differs by the position of the fuel nozzle. The gas turbine combustor according to the present invention includes a burner provided with a fuel nozzle group having a plurality of fuel nozzles for fuel supply, a fuel nozzle plate structurally supporting the fuel nozzles and serving to distribute the fuel flowing from an upstream side to the fuel nozzles, and a perforated plate located downstream of the fuel nozzles and having nozzle holes corresponding to the fuel nozzles. The fuel nozzle group includes outer circumferential fuel nozzles and inner circumferential fuel nozzles. Each outer diameter of at least a proximal end portion of the outer circumferential fuel nozzles is larger than each outer diameter of the inner circumferential fuel nozzles.

Description

Technical field [0001] The present invention relates to a gas turbine combustor, and more particularly to a gas turbine burner composed of a fuel nozzle plate supported by a plurality of fuel nozzles and structures. Background technique [0002] In the gas turbine, the NOx set strict environmental reference is set in the operation when the load caused by the environment is reduced. [0003] In general, the discharge of NOx increases with the high temperature of the flame temperature, therefore needs to inhibit the formation of a local high temperature flame to achieve uniform combustion. For uniform combustion, a plurality of fuel nozzles for discharge fuel are needed to improve the dispersibility of fuel. [0004] As a prior art document that reduces NOx discharge, Patent Document 1 can be mentioned. [0005] In this Patent Document 1, the following is described in order to reduce the pressure loss in the coaxial nozzle, promote the mixing of the fuel and air to achieve a decrea...

Claims

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More

Application Information

Patent Timeline
no application Login to View More
Patent Type & Authority Applications(China)
IPC IPC(8): F23R3/28F23R3/42
CPCF23R3/283F23R3/42F23R3/286F23R3/343F23R2900/00014F23R3/46F05D2260/964F23R3/28F02C7/22F05D2260/941F05D2260/96F23R2900/00005
Inventor 熊谷理和田山芳英三浦圭祐
Owner MITSUBISHI HEAVY IND LTD
Features
  • R&D
  • Intellectual Property
  • Life Sciences
  • Materials
  • Tech Scout
Why Patsnap Eureka
  • Unparalleled Data Quality
  • Higher Quality Content
  • 60% Fewer Hallucinations
Social media
Patsnap Eureka Blog
Learn More

Browse by: Latest US Patents, China's latest patents, Technical Efficacy Thesaurus, Application Domain, Technology Topic, Popular Technical Reports.

© 2025 PatSnap. All rights reserved.Legal|Privacy policy|Modern Slavery Act Transparency Statement|Sitemap|About US| Contact US: help@patsnap.com