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公开(公告)号：US11125168B2
公开(公告)日：2021-09-21
申请号：US16168934
申请日：2018-10-24
Applicant: United Technologies Corporation
Inventor： Christopher J. Hanlon , James F. Krenzer , Becky E. Rose , Mark F. Zelesky
Abstract: An aspect includes a dirt mitigation system for a gas turbine engine. The dirt mitigation system includes a plurality of bleeds of the gas turbine engine and a control system configured to determine a particulate ingestion estimate indicative of dirt ingested in the gas turbine engine. The control system is further configured to determine one or more operating parameters of the gas turbine engine and alter a bleed control schedule of the gas turbine engine to purge at least a portion of the dirt ingested in the gas turbine engine through one or more of the bleeds of the gas turbine engine based on the particulate ingestion estimate and the one or more operating parameters.
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2.发明申请公开(公告)号：US20180209379A1
公开(公告)日：2018-07-26
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
CPC classification number: F02K3/068 , F01D25/24 , F02C7/04 , F05D2220/36 , F05D2240/303 , F05D2260/40311 , F05D2260/96 , Y02T50/671
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.
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公开(公告)号：US20200240436A1
公开(公告)日：2020-07-30
申请号：US16715528
申请日：2019-12-16
Applicant: United Technologies Corporation
Inventor： Lisa I. Brilliant , Becky E. Rose , Yuan Dong , Stanley J. Balamucki
IPC: F04D29/54 , F04D29/68 , F02K3/04 , F04D29/52 , F04D19/02 , F02K3/06 , F04D25/04 , F04D29/32 , F04D29/56
Abstract: A compressor section for a gas turbine engine according to an example of the present disclosure includes, among other things, a low pressure compressor including a plurality of rotor blades arranged about an axis, a high pressure compressor, and a core flowpath passing through the low pressure compressor. The core flowpath at the low pressure compressor defines an inner diameter and an outer diameter relative to the axis. The outer diameter has a slope angle relative to the axis.
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4.发明授权公开(公告)号：US10301971B2
公开(公告)日：2019-05-28
申请号：US15887136
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
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 no more than 0.45.
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5.发明申请LOW PRESSURE RATIO FAN ENGINE HAVING A DIMENSIONAL RELATIONSHIP BETWEEN INLET AND FAN SIZE 有权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：US20160061057A1
公开(公告)日：2016-03-03
申请号：US13721095
申请日：2012-12-20
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Wesley K. Lord , Robert E. Malecki , Yuan J. Qiu , Becky E. Rose , Jonathan Gilson
CPC classification number: F01D25/24 , F01D5/02 , F01D5/141 , F01D15/12 , F01D17/105 , F02C7/04 , F02K3/06 , F05D2220/32 , F05D2250/00 , F05D2260/40311 , F05D2260/96 , Y02T50/671 , Y02T50/673
Abstract: According to an example embodiment, a gas turbine engine assembly includes, among other things, a fan that has a plurality of fan blades. A diameter of the fan has a dimension D that is based on a dimension of the fan blades. Each fan blade has a leading edge. An inlet portion is situated 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 0.45.
Abstract translation: 根据示例性实施例，燃气涡轮发动机组件尤其包括具有多个风扇叶片的风扇。 风扇的直径具有基于风扇叶片的尺寸的尺寸D. 每个风扇叶片都有一个前沿。 入口部分位于风扇的前方。 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的尺寸关系在约0.2和0.45之间。
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Patent Agency Ranking
6.发明授权公开(公告)号：US09038366B2
公开(公告)日：2015-05-26
申请号：US14067354
申请日：2013-10-30
Applicant: United Technologies Corporation
Inventor： Brian D. Merry , Gabriel L. Suciu , Lisa I. Brilliant , Becky E. Rose , Yuan Dong , Stanley J. Balamucki
CPC classification number: F02C3/13 , F01D5/143 , F01D25/162 , F02C7/36 , F02C9/18 , F02K3/04 , Y02T50/673
Abstract: A gas turbine engine includes a core housing that includes an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flowpath. A shaft provides a rotational axis. A hub is operatively supported by the shaft. A rotor is connected to the hub and supports a compressor section. The compressor section is arranged in a core flow path axially between the inlet case flow path and the intermediate case flow path. The core flowpath has an inner diameter and an outer diameter. At least a portion of inner diameter has an increasing slope angle relative to the rotational axis. A bearing is mounted to the hub and supports the shaft relative to one of the intermediate case and the inlet case.
Abstract translation: 燃气涡轮发动机包括芯壳体，其包括分别设置入口壳体流动路径和中间壳体流路的入口壳体和中间壳体。 轴提供旋转轴。 轮毂由轴可操作地支撑。 转子连接到轮毂并支撑压缩机部分。 压缩机部分布置在轴向上在入口壳体流动路径和中间壳体流动路径之间的芯流动路径中。 核心流路具有内径和外径。 内径的至少一部分相对于旋转轴具有增加的倾斜角。 轴承安装到轮毂上并相对于中间壳体和入口壳体之一支撑轴。
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7.发明授权公开(公告)号：US09920653B2
公开(公告)日：2018-03-20
申请号：US13721095
申请日：2012-12-20
Applicant: United Technologies Corporation
Inventor： Wesley K. Lord , Robert E. Malecki , Yuan J. Qiu , Becky E. Rose , Jonathan Gilson
CPC classification number: F01D25/24 , F01D5/02 , F01D5/141 , F01D15/12 , F01D17/105 , F02C7/04 , F02K3/06 , F05D2220/32 , F05D2250/00 , F05D2260/40311 , F05D2260/96 , Y02T50/671 , Y02T50/673
Abstract: According to an example embodiment, a gas turbine engine assembly includes, among other things, a fan that has a plurality of fan blades. A diameter of the fan has a dimension D that is based on a dimension of the fan blades. Each fan blade has a leading edge. An inlet portion is situated 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 0.45.
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8.发明申请公开(公告)号：US20140248129A1
公开(公告)日：2014-09-04
申请号：US14067354
申请日：2013-10-30
Applicant: United Technologies Corporation
Inventor： Brian D. Merry , Gabriel L. Suciu , Lisa I. Brilliant , Becky E. Rose , Yuan Dong , Stanley J. Balamucki
IPC: F02C3/13
CPC classification number: F02C3/13 , F01D5/143 , F01D25/162 , F02C7/36 , F02C9/18 , F02K3/04 , Y02T50/673
Abstract: A gas turbine engine includes a core housing that includes an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flowpath. A shaft provides a rotational axis. A hub is operatively supported by the shaft. A rotor is connected to the hub and supports a compressor section. The compressor section is arranged in a core flow path axially between the inlet case flow path and the intermediate case flow path. The core flowpath has an inner diameter and an outer diameter. At least a portion of inner diameter has an increasing slope angle relative to the rotational axis. A bearing is mounted to the hub and supports the shaft relative to one of the intermediate case and the inlet case.
Abstract translation: 燃气涡轮发动机包括芯壳体，其包括分别设置入口壳体流动路径和中间壳体流路的入口壳体和中间壳体。 轴提供旋转轴。 轮毂由轴可操作地支撑。 转子连接到轮毂并支撑压缩机部分。 压缩机部分布置在轴向上在入口壳体流动路径和中间壳体流动路径之间的芯流动路径中。 核心流路具有内径和外径。 内径的至少一部分相对于旋转轴具有增加的倾斜角。 轴承安装到轮毂上并相对于中间壳体和入口壳体之一支撑轴。
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公开(公告)号：US11261800B2
公开(公告)日：2022-03-01
申请号：US16168943
申请日：2018-10-24
Applicant: United Technologies Corporation
Inventor： Christopher J. Hanlon , James F. Krenzer , Becky E. Rose , Mark F. Zelesky
Abstract: An aspect includes a system for a gas turbine engine. The system includes one or more bleeds of the gas turbine engine and a control system configured to check one or more activation conditions of a dirt rejection mode in the gas turbine engine. A bleed control schedule of the gas turbine engine is adjusted to extend a time to hold the one or more bleeds of the gas turbine engine partially open at a power setting above a threshold based on the one or more activation conditions. One or more deactivation conditions of the dirt rejection mode in the gas turbine engine are checked. The dirt rejection mode is deactivated to fully close the one or more bleeds based on the one or more deactivation conditions.
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10.发明授权公开(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
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.
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