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公开(公告)号：WO2020190280A1
公开(公告)日：2020-09-24
申请号：PCT/US2019/022901
申请日：2019-03-19
Applicant: DRESSER-RAND COMPANY
Abstract: A turbine (10) includes a disk (25) having a plurality of protrusions (120) arranged such that any two adjacent protrusions (120) define an axial entry fir tree space (125), each protrusion (120) defining an outermost lobe (165) having an outermost surface (150) and an axial length. A turbine blade (30) includes an airfoil (170), a platform (175), and a blade root (180) having a fir tree arranged to engage a leading protrusion (135) and a trailing protrusion (140). The blade root (180) and the leading protrusion (135) cooperate to define a leading gap (200), and the blade root (180) and the trailing protrusion (140) cooperate to define a trailing gap (215). A leading plug (220) is disposed in the leading gap (200) and a trailing plug (225) is disposed in the trailing gap (215). Each of the leading plug (220) and the trailing plug (225) have a plug (220) length that is at least as great as the axial length.
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2.发明申请
公开(公告)号：WO2020142113A1
公开(公告)日：2020-07-09
申请号：PCT/US2019/045436
申请日：2019-08-07
Applicant: DRESSER-RAND COMPANY
Inventor： VACHON, Nicholas
Abstract: A platform seal and damper assembly for turbomachinery (100), such as fluidized catalytic cracking (FCC) expanders or gas turbine engines; and methodologies for forming such assembly are provided. An axially-extending groove (160) is arranged on a side (162) of a respective platform. Groove (160) is defined by a radially-outward surface (168) at an underside of the platform and a surface (170) extending with a tangential component (T) toward radially-outward surface (168). A seal and damper member (152) is disposed in groove (160), where the body of seal and damper member has adjoining surfaces (190, 188) configured to respectively engage, in response to a camming action, with the surfaces (168, 170) that define the axially-extending groove. The camming action being effective to produce an interference fit of the seal and damper member (152) with the side of the respective platform (162) and an opposed side (163) of an adjacent platform.
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3.发明申请
公开(公告)号：WO2017136625A1
公开(公告)日：2017-08-10
申请号：PCT/US2017/016348
申请日：2017-02-03
Applicant: DRESSER-RAND COMPANY
Inventor： GRIFFIN, Timothy R. , SEAMON, George H. , VACHON, Nicholas
CPC classification number: F01D5/081 , C10G11/18 , C10G75/00 , C10G2300/4006 , F01D5/082 , F01D5/3038 , F01D11/001 , F01D11/006 , F01D25/24 , F05D2230/60 , F05D2260/22141
Abstract: System and method for cooling an expander (100) rotor assembly. The system may include an annular body (148) disposed on a rotor disc (128) of the rotor assembly (118). The rotor disc (128) may also include a plurality of rotor blades (140) mounted thereto via respective roots (142). The annular body may define at least one fluid passageway fluidly coupling the roots (142) and the cooling source (112). The annular ring (148) may be configured to prevent mixing of the flue gas (F) with a coolant (C) provided by the cooling source (112) and flowing through the at least one fluid passageway and contacting at least one root (142). The system may also include a plurality of seal members (192, 292), each disposed between respective platforms (146) of adjacent rotor blades (140) and configured to prevent flue gas (F) flowing though the expander (100) from mixing with the coolant (C).
Abstract translation: 用于冷却膨胀机（100）转子组件的系统和方法。 该系统可以包括设置在转子组件（118）的转子盘（128）上的环形主体（148）。 转子盘（128）还可以包括经由相应的根部（142）安装到其上的多个转子叶片（140）。 环形主体可限定流体地联接根部（142）和冷却源（112）的至少一个流体通道。 环形环（148）可构造成防止烟道气（F）与由冷却源（112）提供的冷却剂（C）混合并流过至少一个流体通道并接触至少一个根部（142 ）。 该系统还可以包括多个密封构件（192,292），每个密封构件设置在相邻转子叶片（140）的相应平台（146）之间并且被配置为防止流过膨胀器（100）的烟道气（F）与 冷却液（C）。
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4.发明公开
公开(公告)号：EP3887651A1
公开(公告)日：2021-10-06
申请号：EP19880966.7
申请日：2019-08-07
Applicant: Dresser-Rand Company
Inventor： VACHON, Nicholas
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