中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

18 records (took 0.014 seconds)

    Low pressure ratio fan engine having a dimensional relationship between inlet and fan size
    1.
    发明授权
    Low pressure ratio fan engine having a dimensional relationship between inlet and fan size 有权

    公开(公告)号：US11015550B2

    公开(公告)日：2021-05-25

    申请号：US15887183

    申请日：2018-02-02

    Applicant: United Technologies Corporation

    Inventor： Wesley K. Lord ,  Robert E. Malecki ,  Yuan J. Qiu ,  Becky E. Rose ,  Jonathan Gilson

    IPC: F02K3/068 ,  F01D25/24 ,  F02C7/04

    Abstract: According to an example embodiment, a gas turbine engine assembly includes, among other things, a fan section including a fan, the fan including a plurality of fan blades, a diameter of the fan having a dimension D that is based on a dimension of the fan blades, each fan blade having a leading edge, and a forward most portion on the leading edges of the fan blades in a first reference plane, a turbine section including a high pressure turbine and a low pressure turbine, the low pressure turbine driving the fan, a nacelle including an inlet portion forward of the fan, a forward edge on the inlet portion in a second reference plane, and a length of the inlet portion having a dimension L measured along an engine axis between the first reference plane and the second reference plane. A dimensional relationship of L/D is no more than 0.45.

    LOW PRESSURE RATIO FAN ENGINE HAVING A DIMENSIONAL RELATIONSHIP BETWEEN INLET AND FAN SIZE
    2.
    发明申请
    LOW PRESSURE RATIO FAN ENGINE HAVING A DIMENSIONAL RELATIONSHIP BETWEEN INLET AND FAN SIZE 审中-公开

    公开(公告)号：US20200025036A1

    公开(公告)日：2020-01-23

    申请号：US16391476

    申请日：2019-04-23

    Applicant: United Technologies Corporation

    Inventor： Wesley K. Lord ,  Robert E. Malecki ,  Yuan J. Qiu ,  Becky E. Rose ,  Jonathan Gilson

    IPC: F01D25/24 ,  F02K3/06 ,  F01D5/14 ,  F02C7/04 ,  F01D5/02 ,  F01D15/12 ,  F01D17/10

    Abstract: According to an example embodiment, a gas turbine engine assembly includes, among other things, a fan section including a fan, the fan including a plurality of fan blades, a diameter of the fan having a dimension D that is based on a dimension of the fan blades, each fan blade having a leading edge, and a forward most portion on the leading edges of the fan blades in a first reference plane, a geared architecture, a turbine section including a high pressure turbine and a low pressure turbine, the low pressure turbine driving the fan through the geared architecture, a nacelle surrounding the fan, the nacelle including an inlet portion forward of the fan, a forward edge on the inlet portion in a second reference plane, and a length of the inlet portion having a dimension L measured along an engine axis between the first reference plane and the second reference plane. A dimensional relationship of L/D is between 0.20 and 0.40.

    LOW PRESSURE RATIO FAN ENGINE HAVING A DIMENSIONAL RELATIONSHIP BETWEEN INLET AND FAN SIZE
    4.
    发明申请
    LOW PRESSURE RATIO FAN ENGINE HAVING A DIMENSIONAL RELATIONSHIP BETWEEN INLET AND FAN SIZE 审中-公开
    低压风扇发动机在入口和风扇尺寸之间存在尺寸关系

    公开(公告)号：US20160108854A1

    公开(公告)日：2016-04-21

    申请号：US14882760

    申请日：2015-10-14

    Applicant: United Technologies Corporation

    Inventor： Wesley K. Lord ,  Robert E. Malecki ,  Yuan J. Qiu ,  Becky E. Rose ,  Jonathan Gilson

    IPC: F02K3/06 ,  F04D19/02 ,  F01D15/12 ,  F01D17/10 ,  F01D5/02 ,  F01D5/12

    CPC classification number: F02K3/06 ,  F01D5/02 ,  F01D5/141 ,  F01D15/12 ,  F01D17/105 ,  F02C7/04 ,  F02C7/045 ,  F04D29/522 ,  F04D29/547 ,  F05D2220/32 ,  F05D2250/00 ,  Y02T50/671 ,  Y02T50/673

    Abstract: A gas turbine engine assembly according to an example of the present disclosure includes, among other things, a fan including a plurality of fan blades, a diameter of the fan having a dimension D that is based on a dimension of the fan blades, each fan blade having a leading edge, a geared architecture configured to drive the fan, a turbine section configured to drive the geared architecture, a compressor section including a first compressor and a second compressor, and an inlet portion forward of the fan. A length of the inlet portion has a dimension L between a location of the leading edge of at least some of the fan blades and a forward edge on the inlet portion. A dimensional relationship of L/D is between about 0.2 and about 0.45.

    Abstract translation: 根据本公开的示例的燃气涡轮发动机组件包括除了别的以外的包括多个风扇叶片的风扇，具有基于风扇叶片的尺寸的尺寸D的风扇的直径，每个风扇 具有前缘的叶片，配置成驱动风扇的齿轮架构，构造成驱动齿轮架构的涡轮部分，包括第一压缩机和第二压缩机的压缩机部分以及风扇前部的入口部分。 入口部分的长度在至少一些风扇叶片的前缘的位置与入口部分的前边缘之间具有尺寸L。 L / D的尺寸关系为约0.2至约0.45。

    Nacelle short inlet
    5.
    发明授权
    Nacelle short inlet 有权

    公开(公告)号：US10724541B2

    公开(公告)日：2020-07-28

    申请号：US15378371

    申请日：2016-12-14

    Applicant: United Technologies Corporation

    Inventor： Yuan J. Qiu ,  Robert E. Malecki ,  Wesley K. Lord

    IPC: F04D29/54 ,  F02C7/04 ,  F02K3/06 ,  B64D33/02 ,  F04D29/32

    Abstract: A fan assembly for a gas turbine engine includes a fan including a plurality of fan blades. Each fan blade extends radially outwardly from a fan hub to a blade tip. The plurality of blade tips define a fan diameter. A nacelle surrounds the fan and defines a fan inlet upstream of the fan, relative to an airflow direction into the fan. The nacelle has a forwardmost edge defining an inlet length from the forwardmost edge to a leading edge of a fan blade of the plurality of fan blades. A ratio of inlet length to fan diameter is between 0.20 and 0.45. A nacelle inner surface defines a nacelle flowpath. The nacelle flowpath has a convex throat portion and a concave diffusion portion between the throat portion and the leading edge of the fan blade at a bottommost portion of the nacelle.

Patent Agency Ranking