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

IPC: F02C7/18 ,  F02C6/08 ,  F01D25/08 ,  F01D25/12 ,  F01D9/06 ,  F01D5/18 ,  F01D5/08

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.

公开(公告)号：US09988986B2

公开(公告)日：2018-06-05

申请号：US14600445

申请日：2015-01-20

Applicant: United Technologies Corporation

Inventor： Nathan Snape ,  Gabriel L. Suciu ,  Brian D. Merry ,  James D. Hill ,  William Ackermann

IPC: F02C7/12

CPC classification number: F02C7/12 ,  F05D2260/213

Abstract: The present disclosure provides systems and methods related to thermal management systems for gas turbine engines. For example, a thermal management system comprises a thermally neutral heat transfer fluid circuit, a first heat exchanger disposed on the fluid circuit, and a second heat exchanger disposed on the fluid circuit.

公开(公告)号：US09963977B2

公开(公告)日：2018-05-08

申请号：US14868903

申请日：2015-09-29

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  James D. Hill ,  Gopal Das

IPC: F01D5/28 ,  F01D5/02 ,  F01D5/14

CPC classification number: F01D5/28 ,  F01D5/02 ,  F01D5/147 ,  F05D2230/23 ,  F05D2230/60 ,  F05D2240/24 ,  F05D2300/174 ,  F05D2300/5023 ,  Y02T50/671

Abstract: Components include a low pressure turbine having a plurality of rotor assemblies including a first gamma TiAl intermetallic blade having a maximum operating temperature over 1180° F. (638° C.). At least two of the rotor assemblies include gamma TiAl intermetallic alloy blades. In an embodiment, a method of making a turbine having a plurality of rotor assemblies includes attaching a first gamma TiAl intermetallic alloy blade to an upstream stage of the plurality of rotor assemblies.

公开(公告)号：US09869183B2

公开(公告)日：2018-01-16

申请号：US14799994

申请日：2015-07-15

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Brian D. Merry ,  James D. Hill ,  Wesley K. Lord

IPC: F01D5/08 ,  F01D5/28

CPC classification number: F01D5/082 ,  F01D5/084 ,  F01D5/085 ,  F01D5/288 ,  Y02T50/672 ,  Y02T50/676

Abstract: A rotor for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a rotor disk rotatable about an axis and a gas path wall coupled to and radially outward of the rotor disk. The gas path wall bounds a radially inward portion of a gas path. A plurality of rotor spokes are radially intermediate the rotor disk and the gas path wall. The plurality of rotor spokes is circumferentially spaced to define a plurality of cooling channels intermediate the rotor disk and the gas path wall. A thermal barrier coating is disposed on a surface of at least one of the plurality of cooling channels. A method of cooling a rotor assembly is also disclosed.

公开(公告)号：US20160369695A1

公开(公告)日：2016-12-22

申请号：US14740636

申请日：2015-06-16

Applicant: United Technologies Corporation

Inventor： Jeffrey F. Perlak ,  Joseph B. Staubach ,  Frederick M. Schwarz ,  James D. Hill

IPC: F02C7/10 ,  F02C3/04 ,  F02C9/18

CPC classification number: F02C7/10 ,  F02C3/04 ,  F02C7/08 ,  F02C9/18 ,  F05D2220/32 ,  F05D2260/20 ,  F05D2270/112 ,  F05D2270/3032 ,  Y02T50/676

Abstract: A recuperated gas turbine engine includes an engine core that has a compressor section, a combustor section, and a turbine section. An exhaust duct is located downstream of the turbine section for receiving a hot turbine exhaust stream from the turbine section. The exhaust duct includes a heat exchanger and a temperature-control module upstream of the heat exchanger. A compressor bleed line leads from the compressor section into the heat exchanger and a compressor return line leads from the heat exchanger into the engine core upstream of the combustor section. The compressor bleed line is operable to selectively feed compressed air to the heat exchanger, and the temperature-control module is operable to selectively modulate at least one of temperature and flow of the hot turbine exhaust stream with respect to the heat exchanger.

Abstract translation: 复原燃气涡轮发动机包括具有压缩机部分，燃烧器部分和涡轮部分的发动机芯。 排气管道位于涡轮机部分的下游，用于从涡轮机部分接收热涡轮机废气流。 排气管道包括在热交换器上游的热交换器和温度控制模块。 压缩机排气管路从压缩机部分引入热交换器，并且压缩机返回管线从热交换器引导到燃烧器部分上游的发动机芯。 压缩机排气管线可操作以选择性地将压缩空气供给到热交换器，并且温度控制模块可操作以选择性地调节热涡轮机废气流相对于热交换器的温度和流量中的至少一个。

公开(公告)号：US20160186666A1

公开(公告)日：2016-06-30

申请号：US14844097

申请日：2015-09-03

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Julian Partyka ,  David R. Pack ,  James D. Hill

IPC: F02C9/18 ,  F02C7/12

CPC classification number: F02C9/18 ,  F01D11/001 ,  F01D11/006 ,  F01D11/04 ,  F02C6/18 ,  F02C7/12 ,  F05D2220/32 ,  F05D2260/20

Abstract: A turbine section for a gas turbine engine includes a first rotor assembly with a first rotor assembly bleed air source and an aft cavity that is in fluid communication with the first rotor assembly bleed air source. A second rotor assembly includes a forward cavity. A vane bleed air source is in fluid communication with the forward cavity. A seal extends between the first rotor assembly and the second rotor assembly.

Abstract translation: 用于燃气涡轮发动机的涡轮部分包括具有第一转子组件放气源的第一转子组件和与第一转子组件放气源流体连通的后腔。 第二转子组件包括前腔。 叶片放气源与前腔流体连通。 密封件在第一转子组件和第二转子组件之间延伸。

公开(公告)号：US20160115866A1

公开(公告)日：2016-04-28

申请号：US14921575

申请日：2015-10-23

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  James D. Hill

IPC: F02C3/14 ,  F01D25/30 ,  F01D25/24 ,  F02C3/04 ,  F02K3/00

Abstract: A gas turbine engine includes a propulsor with a power turbine, a power turbine shaft extending forward therefrom defining a centerline axis, and a fan driven by the power turbine shaft. The fan is aligned with the centerline axis forward of the power turbine and is operatively connected to be driven by the power turbine through the power turbine shaft. A gas generator operatively connected to the propulsor is included downstream from the fan and forward of the power turbine, wherein the gas generator defines a generator axis offset from the centerline axis. The gas generator is operatively connected to the power turbine to supply combustion products for driving the power turbine.

Abstract translation: 燃气涡轮发动机包括具有动力涡轮机的推进器，从其延伸的动力涡轮机轴限定中心线轴线，以及由动力涡轮机轴驱动的风扇。 风扇与动力涡轮机前方的中心线轴线对准，并且可操作地连接以由动力涡轮机通过动力涡轮机轴驱动。 可操作地连接到推进器的气体发生器被包括在风扇的下游并且在动力涡轮机的前方，其中气体发生器限定了偏离中心线轴线的发电机轴线。 气体发生器可操作地连接到动力涡轮机，以供应用于驱动动力涡轮机的燃烧产物。

公开(公告)号：US20160084090A1

公开(公告)日：2016-03-24

申请号：US14844082

申请日：2015-09-03

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Brian D. Merry ,  James D. Hill ,  Mark F. Zelesky

IPC: F01D5/18 ,  F02C3/08 ,  F01D11/00

CPC classification number: F01D5/18 ,  F01D5/06 ,  F01D5/185 ,  F01D5/186 ,  F01D5/187 ,  F01D11/001 ,  F01D11/003 ,  F01D11/005 ,  F02C3/08 ,  F05D2220/32 ,  F05D2260/20 ,  Y02T50/676

Abstract: A turbine section includes a rotor assembly which includes an internal cooling passage. A segmented seal is adjacent the rotor assembly and includes a fluid passage that is in fluid communication with the internal cooling passage.

Abstract translation: 涡轮部分包括包括内部冷却通道的转子组件。 分段密封件邻近转子组件并且包括与内部冷却通道流体连通的流体通道。

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。

公开(公告)号：US20150369130A1

公开(公告)日：2015-12-24

申请号：US14676513

申请日：2015-04-01

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Brian D. Merry ,  James D. Hill

IPC: F02C7/18 ,  F01D25/24

CPC classification number: F02C7/18 ,  F01D5/088 ,  F01D11/001 ,  F01D25/24

Abstract: Systems and methods are disclosed herein for distributing cooling air in gas turbine engines. A tangential on board injector (“TOBI”) may supply cooling air to a turbine section of a gas turbine engine. The cooling air may be split into a first cooling air path and a second cooling air path. The first cooling air path may fluidly connect the TOBI and the interior of a first stage rotor blade. The second cooling air path may fluidly connect the TOBI and a cavity. The cavity may be located between a first disk and a second disk. The cooling air paths from a single cooling air source may thermally isolate portions of the turbine section.

Abstract translation: 本文公开了用于在燃气涡轮发动机中分配冷却空气的系统和方法。 切向喷射器（“TOBI”）可以向燃气涡轮发动机的涡轮部分供应冷却空气。 冷却空气可以分成第一冷却空气通道和第二冷却空气通道。 第一冷却空气路径可以将TOBI和第一级转子叶片的内部流体连接。 第二冷却空气路径可以流体地连接TOBI和空腔。 空腔可以位于第一盘和第二盘之间。 来自单个冷却空气源的冷却空气路径可以热隔离涡轮机部分的部分。