公开(公告)号：WO2013122643A2

公开(公告)日：2013-08-22

申请号：PCT/US2012/066590

申请日：2012-11-27

Applicant: SIEMENS ENERGY, INC. ,  LASTER, Walter R. ,  SCHILP, Reinhard ,  WIEBE, David J.

Inventor： LASTER, Walter R. ,  SCHILP, Reinhard ,  WIEBE, David J.

IPC: F23C9/08

CPC classification number: F23R3/42 ,  F23C9/08 ,  F23R3/26

Abstract: An emissions control system for a gas turbine engine including a flow-directing structure (24) that delivers combustion gases (22) from a burner (32) to a turbine. The emissions control system includes: a conduit (48) configured to establish fluid communication between compressed air (22) and the combustion gases within the flow-directing structure (24). The compressed air (22) is disposed at a location upstream of a combustor head-end and exhibits an intermediate static pressure less than a static pressure of the combustion gases within the combustor (14). During operation of the gas turbine engine a pressure difference between the intermediate static pressure and a static pressure of the combustion gases within the flow-directing structure (24) is effective to generate a fluid flow through the conduit (48).

Abstract translation: 一种用于燃气涡轮发动机的排放控制系统，其包括将燃烧气体（22）从燃烧器（32）输送到涡轮机的流动引导结构（24）。 排放物控制系统包括：导管（48），其配置成建立压缩空气（22）与导流结构（24）内的燃烧气体之间的流体连通。 压缩空气（22）设置在燃烧器头端的上游位置处，并且具有小于燃烧器（14）内的燃烧气体的静压的中间静压力。 在燃气涡轮发动机的操作期间，导流结构（24）内的中间静压与燃烧气体的静压之间的压力差有效地产生通过导管（48）的流体流。

公开(公告)号：WO2013122643A3

公开(公告)日：2013-12-19

申请号：PCT/US2012066590

申请日：2012-11-27

Applicant: SIEMENS ENERGY INC ,  LASTER WALTER R ,  SCHILP REINHARD ,  WIEBE DAVID J

Inventor： LASTER WALTER R ,  SCHILP REINHARD ,  WIEBE DAVID J

IPC: F23R3/42 ,  F23C9/08 ,  F23R3/26

CPC classification number: F23R3/42 ,  F23C9/08 ,  F23R3/26

Abstract: An emissions control system for a gas turbine engine including a flow-directing structure (24) that delivers combustion gases (22) from a burner (32) to a turbine. The emissions control system includes: a conduit (48) configured to establish fluid communication between compressed air (22) and the combustion gases within the flow-directing structure (24). The compressed air (22) is disposed at a location upstream of a combustor head-end and exhibits an intermediate static pressure less than a static pressure of the combustion gases within the combustor (14). During operation of the gas turbine engine a pressure difference between the intermediate static pressure and a static pressure of the combustion gases within the flow-directing structure (24) is effective to generate a fluid flow through the conduit (48).

Abstract translation: 一种用于燃气涡轮发动机的排放控制系统，所述燃气涡轮发动机包括将来自燃烧器（32）的燃烧气体（22）输送到涡轮的流动引导结构（24）。 排放控制系统包括：导管（48），其被配置为建立压缩空气（22）与流动引导结构（24）内的燃烧气体之间的流体连通。 压缩空气（22）设置在燃烧器头端的上游位置处并且表现出小于燃烧器（14）内的燃烧气体的静态压力的中间静压。 在燃气涡轮发动机运行期间，在流动引导结构（24）内的中间静态压力和燃烧气体的静态压力之间的压力差有效地产生通过管道（48）的流体流动。

公开(公告)号：WO2010036286A1

公开(公告)日：2010-04-01

申请号：PCT/US2009/001336

申请日：2009-03-03

Applicant: SIEMENS ENERGY, INC. ,  LASTER, Walter, R. ,  CAI, Weidong ,  FOX, Timothy, A. ,  LANDRY, Kyle, L.

Inventor： LASTER, Walter, R. ,  CAI, Weidong ,  FOX, Timothy, A. ,  LANDRY, Kyle, L.

IPC: F23C7/00 ,  F23R3/14 ,  F23R3/28

CPC classification number: F23C7/004 ,  F23C2900/07001 ,  F23D2900/14021 ,  F23R3/14 ,  F23R3/286

Abstract: A fuel injector (36) for alternate fuels (26A, 26B) with energy densities that differ by at least about a factor of two. Vanes (47B) extend radially from a fuel delivery tube structure (20B) with first and second fuel supply channels (19A, 19B). Each vane has first and second radial passages (21A, 21B) communicating with the respective fuel supply channels, and first and second sets of apertures (23A, 23B) between the respective radial passages and the surface (49) of the vane. The first fuel supply channel, first radial passage, and first apertures form a first fuel delivery pathway providing a first fuel flow rate at a given backpressure. The second fuel supply channel, second radial passage, and second apertures form a second fuel delivery pathway providing a second fuel flow rate that may be at least about twice first fuel flow rate at the given backpressure.

Abstract translation: 一种用于替代燃料（26A，26B）的燃料喷射器（36），其能量密度相差至少约二分之一。 叶片（47B）从具有第一和第二燃料供应通道（19A，19B）的燃料输送管结构（20B）径向延伸。 每个叶片具有与各个燃料供应通道连通的第一和第二径向通道（21A，21B），以及在相应的径向通道和叶片的表面（49）之间的第一组和第二组孔（23A，23B）。 第一燃料供应通道，第一径向通道和第一孔形成在给定背压下提供第一燃料流量的第一燃料输送路径。 第二燃料供应通道，第二径向通道和第二孔形成第二燃料输送路径，其提供第二燃料流量，其可以是在给定背压下的至少约两倍的燃料流速。