公开(公告)号：WO2008090394A2

公开(公告)日：2008-07-31

申请号：PCT/IB2006004323

申请日：2006-12-21

Applicant: ROLLS ROYCE POWER ENG ,  JAY JOHN ,  HARDING SIMON CHARLES

Inventor： JAY JOHN ,  HARDING SIMON CHARLES

CPC classification number: F01D5/141 ,  F05D2220/321 ,  F05D2220/3213 ,  F05D2230/90 ,  F05D2250/74 ,  Y10S416/02

Abstract: The present invention provides an airfoil for a second stage turbine blade having an external surface with first and second sides. The external surface extends spanwise between a hub and a tip and streamwise between a leading edge and a trailing edge of the airfoil. The external surface includes a contour substantially defined by Table 1 as listed in the specification.

Abstract translation: 本发明提供一种用于第二级涡轮机叶片的翼型件，其具有带有第一和第二侧面的外表面。 外表面在毂和尖端之间的翼展方向延伸，并且在翼型的前缘和后缘之间流动地延伸。 外表面包括基本上由说明书中列出的表1所定义的轮廓。

公开(公告)号：WO2007085912A3

公开(公告)日：2007-12-21

申请号：PCT/IB2006004190

申请日：2006-12-22

Applicant: ROLLS ROYCE POWER ENG ,  SALTMAN IVOR ,  WALTERS SEAN ALAN ,  NAPPER ANDREW THOMAS

Inventor： SALTMAN IVOR ,  WALTERS SEAN ALAN ,  NAPPER ANDREW THOMAS

IPC: F01D5/14

CPC classification number: F01D5/141 ,  F01D9/041 ,  F05D2220/3212 ,  F05D2240/122 ,  F05D2240/304 ,  F05D2250/14 ,  F05D2250/74 ,  F05D2260/202 ,  Y02T50/67 ,  Y02T50/672 ,  Y02T50/673 ,  Y02T50/676 ,  Y10S416/05

Abstract: The present invention provides an airfoil (32) for a first stage nozzle guide vane having an external surface with first and second sides. The external surface extends spanwise between a hub and a tip and streamwise between a leading edge (34) and a trailing edge (36) of the airfoil. The external surface includes a contour substantially defined by Table 1 as listed in the specification.

Abstract translation: 本发明提供一种用于第一级喷嘴导向叶片的翼型件（32），其具有带有第一和第二侧面的外表面。 外表面在毂和尖端之间横向延伸，并且在翼型的前缘（34）和后缘（36）之间流动地延伸。 外表面包括基本上由说明书中列出的表1所定义的轮廓。

公开(公告)号：WO2007119115A2

公开(公告)日：2007-10-25

申请号：PCT/IB2006004251

申请日：2006-12-14

Applicant: ROLLS ROYCE POWER ENG ,  SCARINCI THOMAS ,  YOUNG KENNETH JAMES

Inventor： SCARINCI THOMAS ,  YOUNG KENNETH JAMES

CPC classification number: F23R3/346 ,  F23R3/14 ,  F23R3/286 ,  F23R3/36 ,  Y02T50/675

Abstract: One embodiment is a gas turbine engine premix injector including a mixing duct, a plurality of air inlet slots leading to the duct, a plurality of gaseous fuel inlet apertures leading to the duct, a plurality of vanes positioned in the duct downstream from said air inlets, a plurality of liquid fuel inlet apertures leading to the duct, and a plurality of discharge windows positioned between the vanes.

Abstract translation: 一个实施例是一种燃气涡轮发动机预混喷射器，其包括混合管道，通向管道的多个空气入口狭槽，通向管道的多个气体燃料入口孔，多个叶片，其位于管道下游的所述空气入口 ，多个通向管道的液体燃料入口孔和位于叶片之间的多个排出窗口。

公开(公告)号：WO2012090071A8

公开(公告)日：2014-01-03

申请号：PCT/IB2011003329

申请日：2011-12-30

Applicant: ROLLS ROYCE POWER ENG ,  INNES MATTHEW CHRISTOPHER ,  WHENHAM IAN ,  COURBARIAUX YANN ,  BOHAN MARGARET KATHLEEN

Inventor： INNES MATTHEW CHRISTOPHER ,  WHENHAM IAN ,  COURBARIAUX YANN ,  BOHAN MARGARET KATHLEEN

IPC: F23D11/38 ,  B05B7/00 ,  F23D17/00 ,  F23R3/30 ,  F23R3/36

CPC classification number: F02C7/222 ,  B05B7/02 ,  F02C7/22 ,  F23D11/38 ,  F23D14/02 ,  F23D17/002 ,  F23R3/30 ,  F23R3/36

Abstract: A system includes a turbine engine having a fuel injector (100). The fuel injector (100) includes fluid ducts (103,105,107), each having a fuel inlet (108,110,212) coupled to a distinct fuel source. The system includes a compressed air source that provides compressed air simultaneously to the fluid ducts (103,105,107), and a convergence point (106) where combined fuel and air streams from the ducts are mixed. The fuel inlets (108,110, 112) are in a parallel flow arrangement such that no fuel from one fuel inlet (108,110,212) is present at another fuel inlet (108,110,212)

Abstract translation: 一种系统包括具有燃料喷射器（100）的涡轮发动机。 燃料喷射器（100）包括流体管道（103,105,107），每个流体管道具有联接到不同燃料源的燃料入口（108,110,212）。 该系统包括压缩空气源，其同时向流体管道（103,105,107）提供压缩空气，以及汇合点（106），其中来自管道的组合的燃料和空气流混合。 燃料入口（108,110,112）是平行的流动布置，使得在另一个燃料入口（108,110,212）处不存在来自一个燃料入口（108,110,212）的燃料，

公开(公告)号：WO2007116319A3

公开(公告)日：2008-04-03

申请号：PCT/IB2007001571

申请日：2007-01-22

Applicant: ROLLS ROYCE POWER ENG ,  CADIEUX MICHEL

Inventor： CADIEUX MICHEL

IPC: F04D27/02

CPC classification number: F04D27/0215 ,  F01D17/105 ,  F02K3/075 ,  F04D27/023 ,  F05D2250/232 ,  F05D2250/41 ,  F05D2260/50

Abstract: A gas turbine engine system (30) including a plurality of bleed off doors (23) forming a portion of a conical surface in the flow path (60) between the low pressure compressor (62) and the intermediate pressure compressor (63). A plurality of actuators (20) are coupled to a unison ring (31) and move the unison ring in a substantially axial direction. The plurality of bleed off doors are coupled to the unison ring and move therewith.

Abstract translation: 一种燃气涡轮发动机系统（30），包括形成低压压缩机（62）和中压压缩机（63）之间的流路（60）中的锥形表面的一部分的多个排气门（23）。 多个致动器（20）联接到协调环（31）并沿大致轴向移动协调环。 多个排出门被联接到协调环并随之移动。

公开(公告)号：WO2007093851A3

公开(公告)日：2007-11-29

申请号：PCT/IB2006004184

申请日：2006-12-21

Applicant: ROLLS ROYCE POWER ENG ,  CLARKE SAMUEL JOHN

Inventor： CLARKE SAMUEL JOHN

IPC: F01D5/14 ,  F01D9/02

CPC classification number: F01D5/141 ,  F05D2250/70 ,  F05D2250/74 ,  Y02T50/67 ,  Y02T50/672 ,  Y02T50/673 ,  Y10S416/02

Abstract: The present invention provides an airfoil (112) for a third stage nozzle guide vane (110) having an external surface with first and second sides. The external surface extends spanwise between a hub and a tip and streamwise between a leading edge (114) and a trailing edge (116) of the airfoil. The external surface includes a contour substantially defined by Table 1 as listed in the specification.

Abstract translation: 本发明提供一种用于第三级喷嘴引导叶片（110）的翼型件（112），其具有带有第一和第二侧面的外表面。 外表面在毂和尖端之间横向延伸，并且在翼型的前缘（114）和后缘（116）之间流动地延伸。 外表面包括基本上由说明书中列出的表1所定义的轮廓。

公开(公告)号：WO2007141596A2

公开(公告)日：2007-12-13

申请号：PCT/IB2006004272

申请日：2006-12-22

Applicant: ROLLS ROYCE POWER ENG ,  HURST ANDREW JAMES ,  HARDING SIMON CHARLES

Inventor： HURST ANDREW JAMES ,  HARDING SIMON CHARLES

IPC: F01D5/14

CPC classification number: F01D5/141 ,  F05D2250/70 ,  F05D2250/74 ,  Y02T50/67 ,  Y02T50/672 ,  Y02T50/673 ,  Y10T29/4932

Abstract: The present invention provides an airfoil a second stage nozzle guide vane having an external surface with first and second sides. The external surface extends spanwise between a hub and a tip and streamwise between a leading edge and a trailing edge of the airfoil. The external surface includes a contour substantially defined by Table 1 as listed in the specification.

Abstract translation: 本发明提供一种具有第二和第二侧面的外表面的第二级喷嘴引导叶片的翼型件。 外表面在毂和尖端之间的翼展方向延伸，并且在翼型的前缘和后缘之间流动地延伸。 外表面包括基本上由说明书中列出的表1所定义的轮廓。

公开(公告)号：WO2008125907A3

公开(公告)日：2009-05-28

申请号：PCT/IB2007004564

申请日：2007-10-26

Applicant: ROLLS ROYCE POWER ENG ,  INNES MATTHEW CHRISTOPHER ,  OMIELAN WALTER KASIMIERZ ,  HAMBY RICHARD JOHN

Inventor： INNES MATTHEW CHRISTOPHER ,  OMIELAN WALTER KASIMIERZ ,  HAMBY RICHARD JOHN

IPC: F23R3/34 ,  F23N5/20 ,  F23R3/36

CPC classification number: F02C7/22 ,  F02M21/042 ,  F05D2260/607 ,  F23C2900/07022 ,  F23D2206/10 ,  F23D2209/30 ,  F23K2301/203 ,  F23N5/203 ,  F23N2027/04 ,  F23N2027/06 ,  F23N2037/08 ,  F23R3/34 ,  F23R3/36

Abstract: One aspect relates to an apparatus having a combustion chamber and a duct in fluid flow communication with the combustion chamber. The apparatus includes at least one opening adapted for delivering a liquid fuel into the duct. The apparatus further includes at least one passage adapted for delivery of a gas upstream of the at least one opening for minimizing the entrance of a fluid other than the gas into the fuel delivery opening.

Abstract translation: 一个方面涉及一种具有燃烧室和与燃烧室流体连通的管道的设备。 该装置包括适于将液体燃料输送到管道中的至少一个开口。 该装置还包括至少一个通道，其适于在至少一个开口的上游输送气体，以最小化除气体之外的流体进入燃料输送口。

公开(公告)号：WO2008035135A3

公开(公告)日：2008-08-14

申请号：PCT/IB2006004082

申请日：2006-12-21

Applicant: ROLLS ROYCE POWER ENG ,  SADLER KEITH ,  NAPPER ANDREW THOMAS

Inventor： SADLER KEITH ,  NAPPER ANDREW THOMAS

IPC: F01D5/14

CPC classification number: F01D5/141 ,  F05D2250/70 ,  F05D2250/74 ,  Y10S416/02

Abstract: The present invention provides an airfoil for a first stage turbine blade having an external surface with first and second sides. The external surface extends spanwise between a hub and a tip and streamwise between a leading edge and a trailing edge of the airfoil. The external surface includes a contour substantially defined by Table 1 as listed in the specification.

Abstract translation: 本发明提供了用于第一级涡轮机叶片的翼型，其具有带第一和第二侧面的外表面。 外表面在毂和尖端之间沿翼展方向延伸并且在翼型的前缘和后缘之间沿流动方向延伸。 外表面包括由说明书中列出的表1基本上限定的轮廓。

公开(公告)号：WO2007125382A3

公开(公告)日：2008-01-03

申请号：PCT/IB2006004106

申请日：2006-12-20

Applicant: ROLLS ROYCE POWER ENG ,  SHEFFIELD MARK

Inventor： SHEFFIELD MARK

IPC: F01D5/14

CPC classification number: F01D5/141 ,  F05D2220/321 ,  F05D2220/3213 ,  F05D2220/3215 ,  F05D2250/74

Abstract: The present invention provides an airfoil for a third stage blade (138) having an external surface with first and second sides. The external surface extends spanwise between a hub (352) and a tip (354) and streamwise between a leading edge (140) and a trailing edge (142) of the airfoil. The external surface includes a contour substantially defined by Table 1 as listed in the s specification.

Abstract translation: 本发明提供了一种具有第一和第二侧面的外表面的第三级叶片（138）的翼型件。 外表面在翼片（352）和尖端（354）之间横向延伸并且在翼型件的前缘（140）和后缘（142）之间流动地延伸。 外表面包括由本说明书中列出的基本上由表1定义的轮廓。