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1. 发明授权

US06619030B1 Aircraft engine with inter-turbine engine frame supported counter rotating low pressure turbine rotors 有权
标题翻译：具有涡轮机内引擎框架的飞机发动机支持反转低压涡轮转子
公开(公告)号：US06619030B1
公开(公告)日：2003-09-16
申请号：US10087681
申请日：2002-03-01
申请人： Jorge F. Seda , Lawrence W. Dunbar , Philip R. Gliebe , Peter N. Szucs , John C. Brauer , James E. Johnson , Thomas Moniz , Gregory T. Steinmetz
发明人： Jorge F. Seda , Lawrence W. Dunbar , Philip R. Gliebe , Peter N. Szucs , John C. Brauer , James E. Johnson , Thomas Moniz , Gregory T. Steinmetz
IPC分类号： F02K302
CPC分类号： F02K3/072 , F01D9/041 , F01D11/001 , F01D25/16 , F01D25/18 , F01D25/24 , F02C3/067 , F02C7/20 , F05D2240/56 , Y02T50/672
摘要： An aircraft gas turbine engine assembly includes an inter-turbine frame axially located between high and low pressure turbines. Low pressure turbine has counter rotating low pressure inner and outer rotors with low pressure inner and outer shafts which are at least in part rotatably disposed co-axially within a high pressure rotor. Inter-turbine frame includes radially spaced apart radially outer first and inner second structural rings disposed co-axially about a centerline and connected by a plurality of circumferentially spaced apart struts. Forward and aft sump members having forward and aft central bores are fixedly joined to axially spaced apart forward and aft portions of the inter-turbine frame. Low pressure inner and outer rotors are rotatably supported by a second turbine frame bearing mounted in aft central bore of aft sump member. A mount for connecting the engine to an aircraft is located on first structural ring.
摘要翻译：飞机燃气涡轮发动机组件包括轴向位于高压和低压涡轮机之间的涡轮机间框架。低压涡轮机具有相对转动的低压内转子和外转子，其具有低压内外轴，其至少部分地可旋转地设置在高压转子内。涡轮机外框架包括径向间隔开的径向外部第一和第二结构环，所述第一和第二结构环围绕中心线共轴设置并且通过多个周向间隔开的支柱连接。具有前中心孔和后中心孔的前后贮槽构件固定地连接到涡轮机间框架的轴向间隔开的前部和后部。低压内转子和外转子由安装在船尾组件的后中心孔的第二涡轮机框架轴承可旋转地支撑。用于将发动机连接到飞行器的安装座位于第一结构环上。

2. 发明授权

US06732502B2 Counter rotating aircraft gas turbine engine with high overall pressure ratio compressor 有权
标题翻译：具有高整体压力比压缩机的反转式飞机燃气轮机
公开(公告)号：US06732502B2
公开(公告)日：2004-05-11
申请号：US10087428
申请日：2002-03-01
申请人： Jorge F. Seda , Lawrence W. Dunbar , Peter N. Szucs , John C. Brauer , James E. Johnson
发明人： Jorge F. Seda , Lawrence W. Dunbar , Peter N. Szucs , John C. Brauer , James E. Johnson
IPC分类号： F02K304
CPC分类号： F04D19/024 , F01D5/03 , F02K3/072 , F05D2240/12 , F05D2250/52 , Y02T50/672 , Y02T50/673
摘要： An aircraft gas turbine engine includes high and low pressure turbines having respective counter rotatable low pressure inner and outer rotors with low pressure inner and outer shafts in part rotatably disposed co-axially within a high pressure rotor and drivingly connected to first and second fan blade rows and first and second boosters respectively. A bypass duct radially bounded by a fan casing and an annular radially inner bypass duct wall surrounds the boosters axially located between the first and second fan blade rows. The engine has a high pressure compressor operable to produce an overall pressure ratio in a range of about 40-65 and a fan inlet hub to tip radius ratio in a range between 0.20 and 0.35, a bypass ratio in a range of 5-15, an operational fan pressure ratio in a range of 1.4-2.5, and a sum of operational fan tip speeds in a range of 1000 to 2500 feet per second.
摘要翻译：飞机燃气涡轮发动机包括高低压涡轮机，其具有相应的可反转的低压内转子和外转子，其中低压内和外转子部分可旋转地同轴地设置在高压转子内并且驱动地连接到第一和第二风扇叶片排和第一和第二增压器。由风扇壳体和环形径向内部旁路管道壁径向界定的旁路管道围绕轴向位于第一和第二风扇叶片排之间的增压器。发动机具有高压压缩机，其可操作以产生在大约40-65范围内的总体压力比和风扇入口毂与尖端半径比在0.20和0.35之间的范围内，旁路比在5-15的范围内，操作风扇压力比在1.4-2.5的范围内，以及在1000至2500英尺每秒的范围内的操作风扇叶尖速度的总和。

3. 发明授权

US06220012B1 Booster recirculation passageway and methods for recirculating air 失效
标题翻译：增压循环通道和循环空气的方法
公开(公告)号：US06220012B1
公开(公告)日：2001-04-24
申请号：US09309014
申请日：1999-05-10
申请人： Ambrose A. Hauser , Peter N. Szucs , Jorge F. Seda
发明人： Ambrose A. Hauser , Peter N. Szucs , Jorge F. Seda
IPC分类号： F02G1310
CPC分类号： F04D27/02 , F01D5/145 , F04D29/164 , F04D29/526 , F04D29/685
摘要： A recirculation passageway for a turbine engine provides stall protection in a booster by directing high pressure airflow from a flow path of the booster to the passageway. The high pressure airflow loses energy and decreases in pressure while traveling through the passageway until re-entry into the booster flow path. The airflow recirculates in the passageway until the airflow is discharged through a high pressure compressor.
摘要翻译：用于涡轮发动机的再循环通道通过将高压气流从增压器的流动路径引导到通道来在增压器中提供失速保护。高压气流在通过通道的同时会损失能量并降低压力，直到重新进入增压器流路。气流在通道中再循环，直到气流通过高压压缩机排出。

4. 发明授权

US06328533B1 Swept barrel airfoil 有权
标题翻译：扫管筒翼型
公开(公告)号：US06328533B1
公开(公告)日：2001-12-11
申请号：US09467956
申请日：1999-12-21
申请人： John J. Decker , Andrew Breeze-Stringfellow , Gregory T. Steinmetz , Peter N. Szucs
发明人： John J. Decker , Andrew Breeze-Stringfellow , Gregory T. Steinmetz , Peter N. Szucs
IPC分类号： F01D514
CPC分类号： F04D29/324 , F01D5/141 , F05D2250/71
摘要： An airfoil includes a leading edge chord barrel between a root and a tip, and forward aerodynamic sweep at the tip.
摘要翻译：翼型件包括在根部和尖端之间的前缘弦杆筒，以及尖端处的向前空气动力学扫掠。

5. 发明授权

US5809772A Turbofan engine with a core driven supercharged bypass duct 失效
标题翻译： Turbofan发动机带有核心驱动的增压旁路管道
公开(公告)号：US5809772A
公开(公告)日：1998-09-22
申请号：US625498
申请日：1996-03-29
申请人： Rollin G. Giffin, III , James E. Johnson , David W. Crall , John W. Salvage , Peter N. Szucs
发明人： Rollin G. Giffin, III , James E. Johnson , David W. Crall , John W. Salvage , Peter N. Szucs
IPC分类号： F02K3/075 , F02K3/02 , F02K3/07
CPC分类号： F02K3/075
摘要： A multiple bypass turbofan engine including a core engine assembly has a fan bypass duct radially outward of the core engine assembly and has first and second inlets disposed between forward and aft fans driven by a low pressure turbine and a core engine turbine respectively. An inlet duct having an annular duct wall is disposed radially inward of the bypass duct and connects the second inlet to the bypass duct and has disposed within a supercharger means for compressing air which is drivingly connected to the core turbine. One embodiment of the aft fan may have radially inner and outer rows of aft fan vane airfoils separated by a non-rotatable portion of the annular duct wall such that the outer row of aft fan vane airfoils are disposed in the inlet duct and at least one of the aft fan vane airfoils is and, preferably, all of which are, independently variable. Radially inner and outer rows of aft fan rotor blade airfoils separated by a rotatable portion of the annular duct wall such that the outer row of aft fan rotor blade airfoils are disposed in the inlet duct adjacent to and longitudinally aft of radially inner and outer rows of aft fan vane airfoils, respectively. The radially outer rows of aft fan vane and rotor blade airfoils provide the supercharger means.
摘要翻译：包括核心发动机组件的多旁路涡扇发动机发动机具有在核心发动机组件的径向外侧的风扇旁通管道，并且分别设置有由低压涡轮机和核心发动机涡轮机驱动的前后风扇之间的第一和第二入口。具有环形管道壁的入口管路设置在旁路管道的径向内侧，并将第二入口连接到旁路管道，并且设置在增压器装置中，用于压缩驱动地连接到核心涡轮机的空气。后风扇的一个实施例可以具有由环形管道壁的不可旋转部分分开的后排风扇叶片翼片的径向内部和外部排，使得外部行的后部风扇叶片翼型件设置在入口管道中，并且至少一个后翼形叶片翼型件，并且优选地，所有这些都是独立可变的。前后风扇转子叶片翼片的内排和外排由环形管道壁的可旋转部分分开，使得外排风扇转子叶片翼型件的外排设置在入口管道中，并且沿径向的内排和外排后扇叶片翼型。后风扇叶片和转子叶片翼型件的径向外排提供增压装置。

6. 发明授权

US06195983B1 Leaned and swept fan outlet guide vanes 有权
标题翻译：倾斜风扇出风口导叶
公开(公告)号：US06195983B1
公开(公告)日：2001-03-06
申请号：US09248894
申请日：1999-02-12
申请人： Aspi R. Wadia , Peter N. Szucs , Bruce A. Hemmelgarn
发明人： Aspi R. Wadia , Peter N. Szucs , Bruce A. Hemmelgarn
IPC分类号： F02K302
CPC分类号： F01D5/141 , F04D29/544 , F05D2250/70 , Y02T50/673
摘要： A gas turbine engine fan assembly has a plurality of axially swept fan exit guide vanes circumferentially disposed around an axially extending centerline, a plurality of fan frame struts having axially swept strut leading edges and circumferentially disposed around the centerline directly aft of the exit guide vanes, and an axially extending annular gap between the trailing edges of the fan exit guide vanes and the strut leading edges. Each of the fan exit guide vanes has pressure and suction sides, vane trailing edges, and is circumferentially leaned such that the pressure side facing radially inward. Preferably, the axially swept vane trailing edges and the axially swept strut leading edges generally conform to each other in shape. An annular splitter is radially disposed at a spanwise position to split airflow from the fan into fan bypass airflow and core engine airflow and includes a splitter leading edge preferably positioned aft of the strut leading edges.
摘要翻译：燃气涡轮发动机风扇组件具有围绕轴向延伸的中心线周向设置的多个轴向扫掠的风扇出口导向叶片，多个风扇框架支柱具有轴向扫掠的支柱前缘并且周向地设置在出口导向叶片的直接后方的中心线周围，以及在风扇出口导向叶片的后缘和支柱前缘之间的轴向延伸的环形间隙。每个风扇出口导叶具有压力和吸力侧，叶片后缘，并且周向倾斜，使得压力侧面向径向向内。优选地，轴向扫掠的叶片后缘和轴向扫掠的支柱前缘通常在形状上彼此适配。环形分离器径向设置在翼展方向位置，以将来自风扇的气流分成风扇旁路气流和核心发动机气流，并且包括优选地定位在支柱前缘的后方的分流器前缘。

7. 发明授权

US07413401B2 Methods and apparatus for controlling variable stator vanes 失效
标题翻译：用于控制可变定子叶片的方法和装置
公开(公告)号：US07413401B2
公开(公告)日：2008-08-19
申请号：US11333591
申请日：2006-01-17
申请人： Peter N. Szucs , Andrew Breeze-Stringfellow
发明人： Peter N. Szucs , Andrew Breeze-Stringfellow
IPC分类号： F03B3/18
CPC分类号： F01D17/162 , F04D29/563 , F05D2250/71 , F05D2260/50 , F05D2260/53 , F05D2260/56 , F05D2260/70 , F05D2260/74
摘要： An actuation system for a plurality of variable stator vanes pivotally mounted in a casing of a compressor. The system includes a plurality of levers each having a proximal end and an opposite distal end. Each of the proximal ends are fixedly coupled to a corresponding stator vane of the plurality of variable stator vanes for pivoting the corresponding stator vane about a stator vane axis. The system also includes an actuation ring coaxially surrounding the casing adjacent the plurality of levers. The actuation ring is coupled to the distal ends of each of the plurality of levers for pivoting the levers as the actuation ring is rotated about a compressor rotation axis. The actuation ring includes a pin extending outward from a radially outward surface of the actuation ring. The system also includes a template comprising a slot for receiving at least a portion of the actuation ring pin. The slot includes a shape configured to guide rotation of the actuation ring about the compressor rotation axis when the template is moved relative to the actuation ring.
摘要翻译：用于可枢转地安装在压缩机壳体中的多个可变定子叶片的致动系统。该系统包括多个杠杆，每个杠杆具有近端和相对的远端。每个近端固定地联接到多个可变定子叶片中的对应的定子叶片，用于围绕定子叶片轴线枢转相应的定子叶片。该系统还包括一个致动环，其致动环同轴地围绕与多个杠杆相邻的壳体。致动环联接到多个杠杆中的每一个的远端，用于当致动环围绕压缩机旋转轴线旋转时枢转杠杆。致动环包括从致动环的径向向外的表面向外延伸的销。该系统还包括模板，其包括用于接收致动环销的至少一部分的槽。狭槽包括形状，其被配置为当模板相对于致动环移动时引导致动环围绕压缩机旋转轴线的旋转。

8. 发明授权

US5167489A Forward swept rotor blade 失效
标题翻译：向前扫掠的转子叶片
公开(公告)号：US5167489A
公开(公告)日：1992-12-01
申请号：US684736
申请日：1991-04-15
申请人： Aspi R. Wadia , Peter N. Szucs , Padmakar M. Niskode , Pamela A. Battle
发明人： Aspi R. Wadia , Peter N. Szucs , Padmakar M. Niskode , Pamela A. Battle
IPC分类号： B64C11/18 , F01D5/14 , F02K3/04 , F04D29/32
CPC分类号： F01D5/141 , B64C11/18 , F02K3/04 , F04D29/324 , Y10S416/02 , Y10S416/05
摘要： A rotor blade includes a root, tip, leading edge, trailing edge, forward surface, and aft surface, and a pitch section disposed equidistantly between the root and tip. The blade has a forward sweep from at least the pitch section to the blade tip relative to incoming streamsurfaces of a fluid flowable over the blade.
摘要翻译：转子叶片包括根部，尖端，前缘，后缘，前表面和后表面以及等距离地设置在根部和尖端之间的节距部分。刀片具有相对于可在叶片上流动的流体的输入流的至少间距部分到叶片尖端的向前扫掠。

9. 发明授权

US06554569B2 Compressor outlet guide vane and diffuser assembly 有权
公开(公告)号：US06554569B2
公开(公告)日：2003-04-29
申请号：US09932323
申请日：2001-08-17
申请人： John J. Decker , Andrew Breeze-Stringfellow , Peter N. Szucs
发明人： John J. Decker , Andrew Breeze-Stringfellow , Peter N. Szucs
IPC分类号： F01D904
CPC分类号： F01D5/141 , F04D29/544 , Y10S415/914
摘要： A gas turbine engine outlet guide vane assembly has annular inner and outer end walls, a flowpath between the inner and outer end walls, outlet guide vanes radially disposed between the inner and outer end walls, and boundary layer energizing means for energizing boundary layers using secondary flow to mix free stream flow into the boundary layers along the inner and outer end walls and suction and pressure sides of the vanes. The boundary layer energizing means includes having the vanes circumferentially leaned in a direction that the suction sides face. The boundary layer energizing means also includes swept leading and/or trailing edges of the vanes that extend radially between the inner and outer end walls. The swept leading and/or trailing edges may be curved inwardly into the vanes from the outer end walls to leading and/or trailing edge points respectively between the end walls. The boundary layer energizing means also includes vanes that are bowed circumferentially outwardly in a circumferential direction and more particularly vanes that are bowed circumferentially outwardly in a circumferential direction the pressure sides face.

10. 发明授权

US06325595B1 High recovery multi-use bleed 失效
标题翻译：高恢复多用途出血
公开(公告)号：US06325595B1
公开(公告)日：2001-12-04
申请号：US09535935
申请日：2000-03-24
申请人： Andrew Breeze-Stringfellow , Peter N. Szucs , Peter J. Wood
发明人： Andrew Breeze-Stringfellow , Peter N. Szucs , Peter J. Wood
IPC分类号： F01D1300
CPC分类号： F04D27/023 , F01D17/10 , F04D29/545
摘要： A compressor air bleed assembly for a gas turbine engine includes a compressor casing surrounding a row of circumferentially spaced compressor blades and defining a flowpath for receiving compressor air flow compressed by the blades. The casing includes a bleed port disposed down stream of at least a row of the blades for receiving a portion of compressed air as bleed airflow. A bleed port, preferably in the form of an annular slot, extends away from the bleed port and has a first throat downstream of the port and a second throat downstream of the first throat. A first duct outlet in the duct leads to a first bleed air circuit, receives a first portion of the bleed airflow, and is disposed between the first and second throats. A second duct outlet in the duct leads to a second bleed air circuit, receives a second portion of the bleed circuit.
摘要翻译：用于燃气涡轮发动机的压缩机排气组件包括围绕一排周向间隔开的压缩机叶片的压缩机壳体，并且限定用于接收由叶片压缩的压缩机空气流的流路。壳体包括设置在至少一排叶片下游的排出口，用于接收一部分压缩空气作为排出气流。优选为环形槽形式的排出口远离排放口延伸，并且在端口下游具有第一喉部，在第一喉部下游具有第二喉管。管道中的第一管道出口通向第一泄放空气回路，接收第一部分排放气流，并设置在第一和第二喉管之间。管道中的第二管道出口通向第二放气回路，接收排放回路的第二部分。

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