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1. 发明公开

EP3519732A1 A TECHNIQUE FOR CONTROLLING OPERATING POINT OF A COMBUSTION SYSTEM BY USING PILOT-AIR 有权转让
公开(公告)号：EP3519732A1
公开(公告)日：2019-08-07
申请号：EP17783401.7
申请日：2017-09-21
申请人： Siemens Aktiengesellschaft
发明人： SADASIVUNI, Suresh
IPC分类号： F23N5/24 , F23R3/34

2. 发明授权

EP2825823B1 GAS TURBINE COMBUSTION SYSTEM AND METHOD OF FLAME STABILIZATION IN SUCH A SYSTEM 有权
标题翻译：燃气轮机燃烧系统和火焰稳定方法在这样的系统
公开(公告)号：EP2825823B1
公开(公告)日：2016-03-23
申请号：EP12798270.0
申请日：2012-12-05
申请人： Siemens Aktiengesellschaft
发明人： SADASIVUNI, Suresh
IPC分类号： F23C7/00 , F23R3/14 , F23R3/28
CPC分类号： F23R3/14 , F23C7/004 , F23C2900/07001 , F23D2900/14021 , F23R3/28 , F23R3/286

3. 发明公开

EP3394514A1 COMBUSTOR FOR A GAS TURBINE 审中-公开
公开(公告)号：EP3394514A1
公开(公告)日：2018-10-31
申请号：EP16812715.7
申请日：2016-12-09
申请人： Siemens Aktiengesellschaft
发明人： HIRD, James , SADASIVUNI, Suresh
IPC分类号： F23R3/14 , F23R3/28 , F23R3/34
CPC分类号： F23R3/14 , F23R3/286 , F23R3/343
摘要： The present invention relates to a combustor (100) for a gas turbine comprising: a pre-combustion chamber (101), a swirler (103), a pilot burner (110) upstream the pre-combustion chamber (101) which comprises a pilot burner surface (111) separating the pilot burner (110) from the pre-combustion chamber (101), the pilot burner (110) further comprising at least a pilot fuel injector (112), wherein the combustor (100) includes a lip (150) extending from the pilot burner surface (111) in the pre-combustion chamber (101), the lip including an internal surface (151) oriented towards the pilot fuel injector (112), the internal surface (151) being inclined of an inclination angle (¸) comprised between 0 degrees and 90 degrees with respect to the centre axis (35) of the pre-combustion chamber (101), and the lip (150) comprises at least a feed passage (155) for connecting the internal surface (151) with the flow (F) of oxidant gas coming from the swirler (103).

4. 发明公开

EP3278029A1 SWIRLER, BURNER AND COMBUSTOR FOR A GAS TURBINE ENGINE 审中-公开
标题翻译：燃气涡轮发动机的SWIRLER，燃烧器和燃烧器
公开(公告)号：EP3278029A1
公开(公告)日：2018-02-07
申请号：EP16710218.5
申请日：2016-03-17
申请人： Siemens Aktiengesellschaft
发明人： SADASIVUNI, Suresh
IPC分类号： F23R3/14 , F23R3/28
CPC分类号： F23R3/14 , F23C2900/07001 , F23R3/286
摘要： The invention relates to a swirler for use in a combustor of a gas turbine engine, comprising a plurality of generally radially inwardly extending passages arranged circumferentially staggered in a circle, each passage having a radially outer inlet end, a radially inner outlet end, first and second generally radially inwardly extending lateral surfaces, and a base surface and top surface, in use of the swirler fuel and air travelling along the passages from their inlet ends to their outlet ends so as to create adjacent to the outlet ends a swirling fuel/air mixture, wherein at least one surface of at least one passage comprises at least one gas fuel injection hole, characterized in that the surface, having the gas fuel injection hole, comprises at least one counterbore radially surrounding the gas fuel injection hole, wherein the gas fuel injection hole is arranged at a base of the counterbore.

5. 发明授权

EP3102877B1 COMBUSTOR 有权
标题翻译：燃烧室
公开(公告)号：EP3102877B1
公开(公告)日：2017-11-15
申请号：EP15700423.5
申请日：2015-01-06
申请人： Siemens Aktiengesellschaft
发明人： BUCHANAN, Eoghan , SADASIVUNI, Suresh
IPC分类号： F23C7/00 , F23Q3/00 , F23R3/14 , F23R3/28 , F23R3/34
CPC分类号： F23R3/286 , F02C7/264 , F05D2220/32 , F05D2240/35 , F23C7/004 , F23C2900/07001 , F23Q3/008 , F23R3/14 , F23R3/343

6. 发明公开

EP3102877A1 COMBUSTOR 有权
标题翻译：燃烧室
公开(公告)号：EP3102877A1
公开(公告)日：2016-12-14
申请号：EP15700423.5
申请日：2015-01-06
申请人： Siemens Aktiengesellschaft
发明人： BUCHANAN, Eoghan , SADASIVUNI, Suresh
IPC分类号： F23C7/00 , F23Q3/00 , F23R3/14 , F23R3/28 , F23R3/34
CPC分类号： F23R3/286 , F02C7/264 , F05D2220/32 , F05D2240/35 , F23C7/004 , F23C2900/07001 , F23Q3/008 , F23R3/14 , F23R3/343
摘要： A burner (30) comprising a pilot burner (58), a combustion chamber, and a swirler (52) located radially outwardly of the combustion chamber and being adapted to impose a swirling motion on a fuel/air mixture about an axial centerline (86) of the combustion chamber, the pilot burner (58) comprising a pilot burner face (60) located radially inwardly of the swirler (52) and forming an axially upstream wall of the combustion chamber, the pilot burner face (60) incorporating a pilot fuel injector (64) and an ignitor (84), both being positioned radially offset from the axial centerline 86, is characterized by a recess (90) being positioned radially offset from the axial centerline (86) within the pilot burner face (60).
摘要翻译：燃烧器（30）包括一个引燃器（58），一个燃烧室和一个旋流器（52），位于燃烧室的径向外侧，适于在燃料/空气混合物周围围绕轴向中心线（86 ），所述引燃燃烧器（58）包括位于所述旋流器（52）的径向内侧并形成所述燃烧室的轴向上游壁的引燃燃烧器面（60），所述引燃燃烧器面（60）结合有引燃器燃料喷射器（64）和点火器（84）都位于径向偏离轴向中心线86的位置，其特征在于凹槽（90）在导向燃烧器面（60）内径向偏离轴向中心线（86）定位，。

7. 发明公开

EP3519734A1 A PILOT BURNER ASSEMBLY WITH PILOT-AIR SUPPLY 有权转让
公开(公告)号：EP3519734A1
公开(公告)日：2019-08-07
申请号：EP17783741.6
申请日：2017-09-22
申请人： Siemens Aktiengesellschaft
发明人： SADASIVUNI, Suresh
IPC分类号： F23R3/34 , F23R3/46 , F23R3/14 , F23R3/28 , F23R3/26

8. 发明公开

EP3519733A1 SWIRLER, COMBUSTOR ASSEMBLY, AND GAS TURBINE WITH IMPROVED FUEL/AIR MIXING 有权转让
公开(公告)号：EP3519733A1
公开(公告)日：2019-08-07
申请号：EP17783398.5
申请日：2017-09-21
申请人： Siemens Aktiengesellschaft
发明人： SADASIVUNI, Suresh
IPC分类号： F23R3/14 , F23R3/28 , F23R3/36 , F23D11/10 , F23D11/38

9. 发明授权

EP2815178B1 INCLINED FUEL INJECTION OF FUEL INTO A SWIRLER SLOT 有权
标题翻译： EINEN WIRBELSCHLITZ GENEIGTE BRENNSTOFFEINSPRITZUNG VON BRENNSTOFF
公开(公告)号：EP2815178B1
公开(公告)日：2016-03-23
申请号：EP12798267.6
申请日：2012-12-04
申请人： Siemens Aktiengesellschaft
发明人： SADASIVUNI, Suresh
IPC分类号： F23C7/00 , F23R3/14 , F23R3/28 , F23R3/34
CPC分类号： F23R3/286 , F02C7/22 , F23C7/004 , F23C2900/07001 , F23D2900/14021 , F23R3/14 , F23R3/343
摘要： The present invention relates to a combustor (100) for a gas turbine. The combustor (100) comprises a pre-combustion chamber (101) having a centre axis (102) and a swirler (103) which is mounted to the pre-combustion chamber (101). The swirler (103) surrounds the pre-combustion chamber (101) in a circumferential direction with respect to the centre axis (102). The swirler (103) comprises a bottom surface (104) which forms a part of a slot (201) through which oxidant/fuel mixture is injectable into the pre-combustion chamber (101), wherein the bottom surface (104) is located in a bottom plane (106). The swirler (103) further comprises a fuel injector (107) which is arranged to the bottom surface (104) such that a fuel is injectable into the slot (201) with a fuel injection direction (108), wherein a first component of the fuel injection direction (108) is non-parallel to the normal (n) of the bottom plane (106).
摘要翻译：本发明涉及一种用于燃气轮机的燃烧器（100）。燃烧器（100）包括具有中心轴线（102）和安装到预燃烧室（101）的旋流器（103）的预燃烧室（101）。旋流器（103）围绕预燃室（101）在相对于中心轴线（102）的圆周方向上包围。旋流器（103）包括形成槽（201）的一部分的底表面（104），氧化剂/燃料混合物可以通过该槽口注入到预燃室（101）中，其中底表面（104）位于底平面（106）。旋流器（103）还包括燃料喷射器（107），燃料喷射器（107）布置在底表面（104）上，使得燃料可以用燃料喷射方向（108）注入到狭槽（201）中，其中第一部件燃料喷射方向（108）不平行于底平面（106）的法线（n）。

10. 发明公开

EP2825823A1 GAS TURBINE COMBUSTION SYSTEM AND METHOD OF FLAME STABILIZATION IN SUCH A SYSTEM 有权
标题翻译：燃气轮机燃烧系统和火焰稳定方法在这样的系统
公开(公告)号：EP2825823A1
公开(公告)日：2015-01-21
申请号：EP12798270.0
申请日：2012-12-05
申请人： Siemens Aktiengesellschaft
发明人： SADASIVUNI, Suresh
IPC分类号： F23C7/00 , F23R3/14 , F23R3/28
CPC分类号： F23R3/14 , F23C7/004 , F23C2900/07001 , F23D2900/14021 , F23R3/28 , F23R3/286
摘要： A gas turbine combustion system (1) which comprises - a first radial inflow swirler (7) having first radial outer intake openings (13), first radial inner outlet openings (15) and first flow passages (11) extending from the first radial outer intake openings (13) to the first radial inner outlet openings (15), each first flow passage (11) including a first angle (a) with respect to the radial direction; - a second radial inflow swirler (17) having second radial outer intake openings (23), second radial inner outlet openings (25) and second flow passages (21) extending from the second radial outer intake openings (23) to the second radial inner outlet openings (25), each second flow passage (21) including a second angle (p) with respect to the radial direction; - where the radial outer circumference of the second radial inflow swirler (17) has a diameter that is smaller than the diameter of the radial inner circumference of the first radial inflow swirler (7) and the second radial inflow swirler (17) is located coaxially with and radially inside the first radial inflow swirler (7). The first angle (a) has a different sign than the second angle (p) with respect to the radial direction.

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