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公开(公告)号：US11131194B2
公开(公告)日：2021-09-28
申请号：US16382776
申请日：2019-04-12
摘要： A rotor assembly for a rotary internal combustion engine is provided. The rotor assembly includes a rotor having a radial groove defined radially in a peripheral surface of the rotor. The groove has a depth and an intermediate shoulder at an intermediate depth. The groove has a first width therealong that is narrower than an intermediate width at the shoulder. An apex seal is received in the groove and protrudes from the peripheral face of the rotor. The apex seal is configured to move radially between a first position and a second position outward of the first position. A biasing member biases the apex seal toward the second position. A platform is disposed in the groove between the apex seal and the biasing member and has a width greater than the first width.
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公开(公告)号：US10907490B2
公开(公告)日：2021-02-02
申请号：US16352019
申请日：2019-03-13
发明人： Roger Huppe , Marc Tardif , Herve Turcotte
摘要： An air supply system is configured to provide cooling air with reduced heat pickup to a turbine rotor of a gas turbine engine. The system comprises a first cooling passage extending between a hollow airfoil and an internal pipe extending through the airfoil. The airfoil extends through a hot gas path. A second cooling passage extends through the internal pipe. The coolant flowing through the second cooling passage is thermally isolated from the airfoil hot surface by the flow of coolant flowing through the first cooling passage. The first and second cooling passages have a common output flow to a rotor cavity of the turbine rotor where coolant flows from the first and second cooling passages combine according to a predetermined ratio.
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公开(公告)号：US10302523B2
公开(公告)日：2019-05-28
申请号：US15167064
申请日：2016-05-27
摘要： The method for testing the integrity of a seal of a cavity in an engine includes providing a sealed test tank external to the cavity, the test tank having an internal volume that is particularly selected, as described herein. A pressure differential is generated between the test tank and the cavity, by creating an initial test pressure within the test tank that is different than an ambient pressure inside the cavity. Gas flow between the test tank and the cavity is then permitted, and a change in pressure within the test tank is measured, as is a test time required for the pressure inside the test tank to reach a reference pressure. The measured test time is compared with a predetermined reference time, and the integrity of the seal may be confirmed when the test time is greater than or equal to the reference time.
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公开(公告)号：US10100730B2
公开(公告)日：2018-10-16
申请号：US14644503
申请日：2015-03-11
发明人： Roger Huppe , Pierre-Yves Legare
摘要： A gas turbine engine including a secondary air system with interconnected fluid passages defining at least one flow path between a common source of pressurized air and a common outlet. Some of the fluid passages deliver the pressurized air to components of the gas turbine engine. The fluid passages include a common fluid passage through which all circulation of the pressurized air to the common outlet passes. The common fluid passage has a section including a venturi configured for controlling a flow of the pressurized air from the source to the outlet. In one embodiment, the venturi is provided in a common inlet or common outlet passage. A method of pressurizing a secondary air system is also discussed.
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公开(公告)号：US09896953B2
公开(公告)日：2018-02-20
申请号：US14570325
申请日：2014-12-15
发明人： Roger Huppe , Jean-Francois Caron
IPC分类号： F01D11/00 , F16J15/16 , F01D25/12 , F16J15/324
CPC分类号： F01D11/003 , F01D25/12 , F05D2260/20 , F16J15/162 , F16J15/324 , Y02T50/675
摘要： A seal runner for a gas turbine engine, the seal runner including an annular body having a sealed cavity defined therein, the cavity being elongated along an axial direction of the body and being annular, the cavity at least partially filled with a coolant, the coolant being liquid across a range of operating temperatures of the gas turbine engine, the coolant having a temperature dependent density across the range of operating temperatures of the gas turbine engine. A gas turbine engine and a method of cooling a seal runner exposed to a temperature gradient are also discussed.
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公开(公告)号：US20170343448A1
公开(公告)日：2017-11-30
申请号：US15167064
申请日：2016-05-27
CPC分类号： G01M3/3281 , G01M3/2869 , G01M15/02 , G01M15/14
摘要： The method for testing the integrity of a seal of a cavity in an engine includes providing a sealed test tank external to the cavity, the test tank having an internal volume that is particularly selected, as described herein. A pressure differential is generated between the test tank and the cavity, by creating an initial test pressure within the test tank that is different than an ambient pressure inside the cavity. Gas flow between the test tank and the cavity is then permitted, and a change in pressure within the test tank is measured, as is a test time required for the pressure inside the test tank to reach a reference pressure. The measured test time is compared with a predetermined reference time, and the integrity of the seal may be confirmed when the test time is greater than or equal to the reference time.
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公开(公告)号：US10273812B2
公开(公告)日：2019-04-30
申请号：US14974338
申请日：2015-12-18
发明人： Roger Huppe , Marc Tardif , Herve Turcotte
摘要： An air supply system is configured to provide cooling air with reduced heat pickup to a turbine rotor of a gas turbine engine. The system comprises a first cooling passage extending between a hollow airfoil and an internal pipe extending through the airfoil. The airfoil extends through a hot gas path. A second cooling passage extends through the internal pipe. The coolant flowing through the second cooling passage is thermally isolated from the airfoil hot surface by the flow of coolant flowing through the first cooling passage. The first and second cooling passages have a common output flow to a rotor cavity of the turbine rotor where coolant flows from the first and second cooling passages combine according to a predetermined ratio.
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公开(公告)号：US09752616B2
公开(公告)日：2017-09-05
申请号：US14670661
申请日：2015-03-27
发明人： Abdelkhalek Saadi , Roger Huppe , Daniel Blais
IPC分类号： F16C27/04 , F16C33/10 , F01D25/18 , F16C37/00 , F16C33/66 , F01D25/16 , F02C7/06 , F16C19/26
CPC分类号： F16C33/1065 , F01D25/16 , F01D25/162 , F01D25/18 , F01D25/183 , F02C7/06 , F16C19/26 , F16C27/045 , F16C33/1045 , F16C33/106 , F16C33/6659 , F16C33/6685 , F16C37/00 , F16C37/007 , F16C2360/23
摘要： A bearing system comprises a bearing configured to be mounted to a shaft. A bearing housing interfaces the bearing to a structure. An annular gap is defined between an outer annular surface of the bearing housing and the structure and configured to receive oil therein. An outlet defined in an outer section surface of the bearing housing is oriented toward a component axially spaced from the bearing. A fluid passageway between the at least one outlet and the annular gap for fluid communication therebetween. In use the fluid passageway directs pressurized oil from the annular gap to the outlet to reach the adjacent component. A method for using oil from a bearing to cool or lubricate a component axially spaced from the bearing is also provided.
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公开(公告)号：US20160169019A1
公开(公告)日：2016-06-16
申请号：US14570325
申请日：2014-12-15
发明人： Roger Huppe , Jean-Francois CARON
CPC分类号： F01D11/003 , F01D25/12 , F05D2260/20 , F16J15/162 , F16J15/324 , Y02T50/675
摘要： A seal runner for a gas turbine engine, the seal runner including an annular body having a sealed cavity defined therein, the cavity being elongated along an axial direction of the body and being annular, the cavity at least partially filled with a coolant, the coolant being liquid across a range of operating temperatures of the gas turbine engine, the coolant having a temperature dependent density across the range of operating temperatures of the gas turbine engine. A gas turbine engine and a method of cooling a seal runner exposed to a temperature gradient are also discussed.
摘要翻译： 一种用于燃气涡轮发动机的密封流道，密封流道包括具有限定在其中的密封空腔的环形体，空腔沿着主体的轴向方向是细长的并且是环形的，空腔至少部分地填充有冷却剂，冷却剂 在燃气涡轮发动机的工作温度的范围内是液体，冷却剂在燃气涡轮发动机的工作温度范围内具有温度依赖密度。 还讨论了燃气涡轮发动机和暴露于温度梯度的密封流道的冷却方法。
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