Gas turbine temperature profiling structure
阅读：60发布：2023-12-21
专利汇可以提供Gas turbine temperature profiling structure专利检索，专利查询，专利分析的服务。并且An axial flow gas turbine having a structure including a fuel nozzle for providing any desired turbine inlet temperature profile according to the mechanical stress on the rotating turbine blades. The fuel nozzle may be a combined multiple fuel gas and liquid type or a single fuel type, an important feature of both being the provision of fuel injection asymmetrically into the combustion chamber to establish a desired ignited fuel temperature pattern therein which continues down to the turbine inlet. This asymmetrical fuel supply into the combustion chamber is obtained by providing a number or size of fuel jets according to the temperature desired; for example, to provide a temperature gradient decreasing in an inward turbine radial direction through the combustor to correspond to the desired turbine blade inlet temperature profile. The angular jet direction also may be varied for different parts of the fuel injection pattern to obtain a further spatial control of the fuel injection distribution into the combustor. These fuel distribution control variables may be used singly or in any combination, and the same or different ones may be used for the gas and liquid jets in multiple fuel nozzles. In addition, a further modification of the intake temperature profile may be obtained by providing relatively cool jets of gaseous fluid through spaced orifices in the radially inner sides of the transition passages which direct the high temperature working gas to the turbine blades.，下面是Gas turbine temperature profiling structure专利的具体信息内容。
1. A high temperature gas supply system for an axial flow turbine having turbine blades arranged to be driven by the high temperature gases and having a combustor with means for igniting fuel supplied thereto, including a fuel supply nozzle comprising a body having a member defining a plurality of fuel outlet spray passages each having a terminal orifice for injecting fuel into the combustor, said terminal orifices being so proportioned that the orifice disposed at the greatest distance from the axis of turbine is larger than the orifice disposed closest to the axis of the turbine and including means for defining a fuel injection pattern for the nozzle of fuel injected into the combustor from said nozzle orifices to provide a substantially predetermined asymmetrical spatial fuel injection pattern transversely of the combustor and a consequent temperature profile of ignited fuel in the combustor.
2. A fuel nozzle for a turbine combustor adapted to supply hot gases to blades of a gas turbine, comprising a body having a member with a spray face and defining a plurality of angularly outwardly extending fuel outlet spray passages each having a terminal orifice in said spray face for injecting fuel into the combustor, said terminal orifices being so proportioned that the orifice disposed at the greatest distance from the axis of the turbine is larger than the orifice disposed closest to the axis of the turbine and said member defining said orifices arranged relative to each other so as to provide a substantially predetermined asymmetrical fuel injection pattern and a consequent temperature profile of ignited fuel transversely of the combustor.
3. A fuel nozzle as defined in claim 2 wherein said member defines said orifices substantially uniformly circumferentially angularly spaced and of a larger size for all orifices in substantially the outer semicircle of the spray face corresponding to substantially the outer half of turbine blades fed by the hot gases from said combustor and of a smaller size for orifices in the complementary inner semicircle of the spray face.
4. A fuel nozzle as defined in claim 2 wherein said member defines said orifices in a progressively graduated size from the smallest at the innermost position of the nozzle orifices relative to the radially inner ends of the turbine blades to the largest orifice at the outermost position of the nozzle orifices relative to said inner ends of the turbine blades.
5. A fuel nozzle as defined in claim 2 wherein said member defines said spray passages at predetermined different outwardly extending angles relative to The longitudinal center line of the nozzle to provide a predetermined larger fuel injection into the combustor toward the outer side thereof relative to the radially inner ends of the turbine blades and a graduated lesser fuel injection toward the opposite side of the combustor.
6. A fuel nozzle as defined in claim 2 wherein said member defines said orifices to provide a substantially larger fuel injection by orifices in the outer semicircle of the spray face relative to the radially inner ends of the turbine blades and a predetermined lesser fuel injection by orifices in the complementary semicircle of the spray face.
7. A fuel nozzle as defined in claim 2 wherein said member defines said orifices to provide a predetermined graduated increase in fuel injection into the combustor from the side thereof nearest to the longitudinal axis of the turbine toward the opposite side thereof.
8. A fuel nozzle as defined in claim 4 wherein said member defines said orifices substantially uniformly circumferentially angularly spaced at a predetermined angle in the outer semicircle of the spray face relative to the longitudinal axis of the turbine and substantially uniformly circumferentially angularly spaced at a larger angle than said predetermined angle in the complementary semicircle of the spray face.
9. A fuel nozzle as defined in claim 5 wherein said member defines said orifices substantially uniformly circumferentially angularly spaced and of a larger substantially uniform size for all orifices in substantially the outer semicircle of the spray face corresponding to substantially the radially outer half of turbine blades fed by hot gases from said combustor and of a smaller substantially uniform size for orifices in the complementary inner semicircle of the nozzle spray face.
10. A fuel nozzle as defined in claim 5 wherein said orifices are arranged in a progressively graduated size from the smallest at the innermost position of the nozzle orifices relative to the longitudinal axis of the turbine to the largest at the outermost position of the nozzle orifices to said turbine axis.
11. A fuel nozzle as defined in claim 5 wherein said member defines said orifices substantially uniformly circumferentially angularly spaced at a predetermined angle in the outer semicircle of the spray face relative to the longitudinal axis of the turbine and substantially circumferentially angularly spaced at a larger angle than said predetermined angle in the complementary inner semicircle of the spray face.
12. A fuel nozzle as defined in claim 5 wherein said spray passage angles are a substantially uniform predetermined value relative to the said nozzle center line in the outer semicircle of the spray face relative to the longitudinal axis of the turbine and are a substantially uniform lesser value than said predetermined value in the complementary inner semicircle of the spray face.
13. A fuel nozzle as defined in claim 5 wherein said spray passage angles are of progressively graduated values from the smallest angle at the innermost passage relative to the longitudinal axis of the turbine to the largest angle at the outermost passage in the nozzle relative to said turbine axis.
14. A fuel nozzle as defined in claim 2 having a second body surrounding and radially spaced from at least a part of the longitudinal sides of said first mentioned member and defining a cylindrical air flow passage therebetween, means providing for the supply of pressurized air to said cylindrical passage, and means for directing pressurized air from said cylindrical passage around fuel injected into the combustor from said spray passage orifices.
15. A fuel nozzle as defined in claim 14 wherein said second body includes means defining a plurality of fuel gas outlet passages each having an orifice for injecting pressurized fuel gas into the combustor around fuel injected thereinto from said spray passage orifices, and means for supplying fuel gas to said fuel gas outlet passages.
16. A Fuel nozzle as defined in claim 15 wherein said fuel gas orifices defining means defines said orifices relative to each other to provide a substantially predetermined asymmetrical fuel gas injection pattern and consequent temperature profile of ignited fuel in the combustor.
17. A turbine high temperature gas supply system as defined in claim 1 having a plurality of combustors arranged in an annular array and having a plurality of transition structures for transmitting the high temperature gases from the combustors to the turbine blades, said transition structures defining a plurality of circumferentially spaced relatively cool pressurized fluid supply passages for directing relatively cool fluid into the high temperature gases to moderate the temperature profile thereof.
18. A turbine high temperature gas supply system as defined in claim 20 having means for directing relatively cool fluid into said transition structures'' cool fluid supply directing passages for progressively decreasing the temperature of the high temperature gas in an inward direction radially of the turbine.
| 标题 | 发布/更新时间 | 阅读量 |
|---|---|---|
| 一种铁锰氧化矿流态化焙烧系统及方法 | 2020-05-08 | 306 |
| 一种天然气燃烧器火焰分层燃烧控制方法 | 2020-05-11 | 755 |
| 一种旋转阀压力调控装置 | 2020-05-11 | 508 |
| 一种基于旋流的流体工质快速加热方法及装置 | 2020-05-08 | 891 |
| 一种双旋风筒浓淡煤粉分离式燃烧器的W火焰锅炉 | 2020-05-08 | 503 |
| 生物质流化床气化烧蒸汽锅炉系统 | 2020-05-08 | 333 |
| 一种可升降的立式燃烧器系统 | 2020-05-11 | 845 |
| 节能聚焰猛火燃烧器 | 2020-05-11 | 257 |
| 逆向热交换燃气采暖炉 | 2020-05-08 | 226 |
| 一种低氮煤粉燃烧器 | 2020-05-08 | 197 |
高效检索全球专利专利汇是专利免费检索,专利查询,专利分析-国家发明专利查询检索分析平台，是提供专利分析，专利查询，专利检索等数据服务功能的知识产权数据服务商。
我们的产品包含105个国家的1.26亿组数据，免费查、免费专利分析。
分析报告
专利汇分析报告产品可以对行业情报数据进行梳理分析，涉及维度包括行业专利基本状况分析、地域分析、技术分析、发明人分析、申请人分析、专利权人分析、失效分析、核心专利分析、法律分析、研发重点分析、企业专利处境分析、技术处境分析、专利寿命分析、企业定位分析、引证分析等超过60个分析角度，系统通过AI智能系统对图表进行解读，只需1分钟，一键生成行业专利分析报告。
旋流燃烧器热门专利
QQ群二维码
意见反馈
意见反馈