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公开(公告)号：US10107126B2
公开(公告)日：2018-10-23
申请号：US14830437
申请日：2015-08-19
Applicant: United Technologies Corporation
Inventor： William K. Ackermann , Clifton J. Crawley, Jr. , Frederick M. Schwarz
Abstract: Assemblies are provided for rotational equipment. One of these assemblies includes a first bladed rotor assembly, a second bladed rotor assembly, a stator vane assembly, a stator structure and a seal assembly. The second bladed rotor assembly includes a rotor disk structure. The stator vane assembly is axially between the first and the second bladed rotor assemblies. The stator structure is mated with and radially within the stator vane assembly. The seal assembly is configured for sealing a gap between the stator structure and the rotor disk structure, wherein the seal assembly includes a non-contact seal.
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公开(公告)号：US10024238B2
公开(公告)日：2018-07-17
申请号：US14594663
申请日：2015-01-12
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Justin J. Phillips , James D. Hill , William K. Ackermann , Chris J. Niggemeier , Gabriel L. Suciu , Anthony R. Bifulco , Julian Partyka
Abstract: A cooling system for providing a buffer cooled cooling air to a turbine section of a gas turbine engine is disclosed. The cooling system may comprise a first conduit configured to transmit a cooling air toward the turbine section, a heat exchanger configured to cool a bleed airflow diverted from the first conduit to provide a buffer air, and a bypass conduit configured to direct at least a portion of the buffer air through at least one passageway that bypasses a bearing compartment of the gas turbine engine. The cooling system may further comprise a manifold configured to allow the cooling air exiting the first conduit and the buffer air exiting the bypass conduit to mix and provide the buffer cooled cooling air, and a nozzle assembly configured to deliver the buffer cooled cooling air to the turbine section.
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53.发明授权公开(公告)号：US09957895B2
公开(公告)日：2018-05-01
申请号：US14771061
申请日：2014-02-28
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , William K. Ackermann
IPC: F02C7/18 , F02C7/06 , F02C7/14 , F01D9/04 , F01D9/06 , F01D5/02 , F02C3/04 , F02C7/04 , F01D25/24 , F04D29/54 , F01D25/12 , F01D17/10 , F02C6/08
CPC classification number: F02C7/18 , F01D5/02 , F01D9/041 , F01D9/065 , F01D17/105 , F01D25/12 , F01D25/24 , F02C3/04 , F02C6/08 , F02C7/04 , F02C7/06 , F02C7/14 , F04D29/541 , F05D2220/32 , F05D2240/12 , F05D2240/35 , F05D2260/20 , F05D2260/213 , Y02T50/676
Abstract: A gas turbine engine is provided that includes a compressor section, a combustor section with a multiple of pre-swirlers, a diffuser case module, and a manifold. The diffuser case module includes a multiple of struts within an annular flow path from said compressor section to said combustor section, wherein at least one of said multiple of struts defines a mid-span pre-diffuser inlet in communication with said annular flow path. The manifold is in communication with said mid-span pre-diffuser inlet and said multiple of pre-swirlers.
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公开(公告)号：US20180094532A1
公开(公告)日：2018-04-05
申请号：US15816512
申请日：2017-11-17
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Michael E. McCune , Jason Husband , Frederick M. Schwarz , Daniel Bernard Kupratis , Gabriel L. Suciu , William K. Ackermann
CPC classification number: F01D15/12 , F01D5/06 , F01D9/041 , F02C3/107 , F02C7/20 , F02C7/36 , F02K3/06 , F04D19/002 , F04D25/045 , F04D29/053 , F04D29/325 , F05D2220/32 , F05D2220/323 , F05D2240/60 , F05D2260/4031 , F05D2260/40311 , F05D2300/501 , Y02T50/671
Abstract: A gas turbine engine includes a fan shaft that has fan blades. A fan shaft is drivingly connected to the fan. A fan shaft support supports the fan shaft and defines a fan shaft support lateral stiffness. A gear system is connected to the fan shaft and driven through an input. A gear system flex mount arrangement accommodates misalignment of the fan shaft and the input during operation and includes a flexible support that defines a flexible support lateral stiffness that is less than 11% of the shaft support lateral stiffness.
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公开(公告)号：US20170306840A1
公开(公告)日：2017-10-26
申请号：US15444808
申请日：2017-02-28
Applicant: United Technologies Corporation
CPC classification number: F02C3/06 , F02C3/04 , F02C7/36 , F02K3/02 , F02K3/04 , F02K3/06 , F02K3/072 , F05D2220/3215
Abstract: A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a performance quantity ratio between about 0.8 and about 1.5.
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Patent Agency Ranking
公开(公告)号：US20170284298A1
公开(公告)日：2017-10-05
申请号：US15091186
申请日：2016-04-05
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Kurt J. Sobanski , William K. Ackermann
Abstract: A low pressure compressor for a gas turbine engine includes a low pressure compressor case extending circumferentially around a central axis of the gas turbine engine. The low pressure compressor case includes an inner radial wall surrounding a low pressure compressor rotor and an outer radial wall at least partially defining a fan bypass passage of the gas turbine engine. A low pressure compressor compartment is located between the inner radial wall and the outer radial wall and an electrical component is located in the low pressure compressor compartment. An inlet port at the outer radial wall is configured to admit a cooling airflow into the low pressure compressor compartment from the fan bypass passage to cool the electrical component.
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公开(公告)号：US09752511B2
公开(公告)日：2017-09-05
申请号：US15484441
申请日：2017-04-11
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Michael E. McCune , Jason Husband , Frederick M. Schwarz , Daniel Bernard Kupratis , Gabriel L. Suciu , William K. Ackermann
CPC classification number: F01D15/12 , F01D5/06 , F01D9/041 , F02C3/107 , F02C7/20 , F02C7/36 , F02K3/06 , F04D19/002 , F04D25/045 , F04D29/053 , F04D29/325 , F05D2220/32 , F05D2220/323 , F05D2240/60 , F05D2260/4031 , F05D2260/40311 , F05D2300/501 , Y02T50/671
Abstract: A gas turbine engine includes a gear system that provides a speed reduction between a fan drive turbine and a fan rotor. Aspects of the gear system are provided with some flexibility. The fan drive turbine has a first exit area and rotates at a first speed. A second turbine section has a second exit area and rotates at a second speed, which is faster than said first speed. A performance quantity can be defined for both turbine sections as the products of the respective areas and respective speeds squared. A performance quantity ratio of the performance quantity for the fan drive turbine to the performance quantity for the second turbine section is relatively high.
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公开(公告)号：US20170051631A1
公开(公告)日：2017-02-23
申请号：US14830514
申请日：2015-08-19
Applicant: United Technologies Corporation
Inventor： William K. Ackermann , Clifton J. Crawley, JR. , Frederick M. Schwarz
CPC classification number: F01D25/12 , F01D5/02 , F01D5/082 , F01D5/3015 , F01D9/041 , F01D11/001 , F01D11/04 , F01D11/08 , F02C3/14 , F02C7/18 , F05D2220/323 , F05D2240/35 , F05D2240/55 , F16J15/442 , Y02T50/671 , Y02T50/673 , Y02T50/676
Abstract: Assemblies are provided for rotational equipment. One of these assemblies includes a bladed rotor assembly, a stator vane assembly, a fixed stator structure and a seal assembly. The bladed rotor assembly includes a rotor disk structure. The stator vane assembly is disposed adjacent the bladed rotor assembly. The fixed stator structure is connected to and radially within the stator vane assembly. The seal assembly is configured for sealing a gap between the stator structure and the rotor disk structure, wherein the seal assembly includes a non-contact seal.
Abstract translation: 为旋转设备提供组件。 这些组件中的一个包括叶片转子组件，定子叶片组件，固定定子结构和密封组件。 叶片转子组件包括转子盘结构。 定子叶片组件设置在叶片转子组件附近。 固定的定子结构连接到定子叶片组件的径向上。 密封组件被构造用于密封定子结构和转子盘结构之间的间隙，其中密封组件包括非接触式密封。
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公开(公告)号：US20160312660A1
公开(公告)日：2016-10-27
申请号：US14696615
申请日：2015-04-27
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： James P. Chasse, JR. , Ryan K. Snyder , William K. Ackermann , Pellegrino J. Pisacreta , Judith F. Brooks , Stephanie Ernst
CPC classification number: F01D25/28 , F01D25/12 , F01D25/14 , F02C7/18 , Y02T50/675
Abstract: A fitting according to an exemplary aspect of the present disclosure includes, among other things, a main body portion having a first axial end and a second axial end opposite the first axial end, an inlet provided at the first axial end, and an outlet adjacent the second axial end. The outlet includes a plurality of circumferentially spaced-apart slots formed through the main body portion, and each slot has an area within a range of 0.52 and 0.59 square inches.
Abstract translation: 根据本公开的示例性方面的配件包括主体部分，其具有第一轴向端部和与第一轴向端部相对的第二轴向端部，设置在第一轴向端部处的入口和邻近的出口 第二个轴向端。 出口包括穿过主体部分形成的多个周向间隔开的槽，并且每个槽具有在0.52和0.59平方英寸的范围内的面积。
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公开(公告)号：US20160076381A1
公开(公告)日：2016-03-17
申请号：US14853392
申请日：2015-09-14
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Brian D. Merry , James D. Hill , William K. Ackermann
IPC: F01D5/18
CPC classification number: F01D5/18 , F01D5/066 , F01D5/084 , F01D5/085 , F04D29/321 , F04D29/584 , F05D2260/205 , F05D2260/221 , Y02T50/671 , Y02T50/676
Abstract: A rotor assembly of a gas turbine engine may be spoked and includes a rotor and a shell. The rotor has a rotor disk and a plurality of blades each having a platform attached to the rotor disk and with a first channel defined radially between the platforms and the rotor disk. The shell projects aft of the rotor and includes inner and outer walls with a passage defined therebetween. The passage is in fluid communication with the first channel and, together, form part of a secondary flowpath for cooling of adjacent components. The rotor assembly may further include a structure located radially inward of the rotor disk and shell. The structure defines a supply conduit for flowing air from the passage and into a rotor bore defined at least in part by adjacent rotor disks. The entering air, being pre-heated when flowing through the channel and passage, warms the bore and reduces thermal gradients, thus thermal fatigue, across the rotor disk.
Abstract translation: 燃气涡轮发动机的转子组件可以被喷射并且包括转子和壳体。 转子具有转子盘和多个叶片，每个叶片具有附接到转子盘的平台，并且在平台和转子盘之间径向地限定第一通道。 壳体在转子的后方突出并且包括具有在其间限定的通道的内壁和外壁。 通道与第一通道流体连通，并且一起形成用于冷却相邻部件的次级流路的一部分。 转子组件还可以包括位于转子盘和壳的径向内侧的结构。 该结构限定用于使空气从通道流入并至少部分地由相邻转子盘限定的转子孔的供应管道。 进入的空气在流过通道和通道时被预热，加热了孔，并降低了转子盘上的热梯度，从而导致热疲劳。
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