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公开(公告)号：US4733527A
公开(公告)日：1988-03-29
申请号：US24817
申请日：1987-03-12
申请人： Harry A. Kidd
发明人： Harry A. Kidd
CPC分类号： F02C3/30 , F02C9/28 , F05D2200/211 , F05D2270/082
摘要： A method and apparatus for automatically maintaining gas turbine NO.sub.x emissions at a substantially constant level during all ambient conditions and for no load to full load fuel flows. The required water/fuel ratio is calculated for a substantially constant level of NO.sub.x emissions at the given operating conditions and, knowing the actual fuel flow to the gas turbine, a signal is generated representing the water metering valve position necessary to inject the proper water flow into the combustor to achieve the desired water/fuel ratio.
摘要翻译： 一种用于在所有环境条件下以及对于满负载燃料流的无负载时将燃气轮机NOx排放物自动维持在基本恒定水平的方法和装置。 对于在给定的操作条件下，基本上恒定的NOx排放水平计算所需的水/燃料比，并且知道到燃气轮机的实际燃料流量，产生代表注入适当水流所必需的水计量阀位置的信号 进入燃烧器以实现所需的水/燃料比。
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公开(公告)号：US20230323837A1
公开(公告)日：2023-10-12
申请号：US17977292
申请日：2022-10-31
IPC分类号： F02K3/06
CPC分类号： F02K3/06 , F05D2200/211 , F05D2200/14 , F05D2220/323
摘要： A gas turbine is provided, the gas turbine engine including a turbomachine having an inlet splitter defining in part an inlet to a working gas flowpath and a fan duct splitter defining in part an inlet to a fan duct flowpath. The gas turbine engine also includes a primary fan driven by the turbomachine defining a primary fan tip radius R1, a primary fan hub radius R2, and a primary fan specific thrust rating TP; and a secondary fan downstream of the primary fan and driven by the turbomachine, the secondary fan defining a secondary fan tip radius R3, a secondary fan hub radius R4, and a secondary fan specific thrust rating TS; wherein the gas turbine engine defines an Effective Bypass Area, and wherein a ratio of R1 to R3 equals
R
1
R
3
=
(
EFP
)
(
1
-
RqR
(
Sec
.
-
Fan
)
2
)
(
1
-
RqR
Prim
.
-
Fan
2
)
(
T
P
T
S
)
(
EBA
)
.-
3.发明授权Bellows units for a chamber of a liquid-propellant rocket engine with afterburning 有权用于具有后燃烧的液体推进剂火箭发动机室的波纹管单元公开(公告)号：US06282887B1
公开(公告)日：2001-09-04
申请号：US09383474
申请日：1999-08-26
申请人： Valentin Georgievich Polushin , Mikhail Ivanovich Osokin , Inna Alexandrovna Kolosova , Khachatur Begoevich Sarafaslanjan , Ivan Denisovich Postnikov
发明人： Valentin Georgievich Polushin , Mikhail Ivanovich Osokin , Inna Alexandrovna Kolosova , Khachatur Begoevich Sarafaslanjan , Ivan Denisovich Postnikov
IPC分类号： F02K942
CPC分类号： F02K9/42 , F02K9/84 , F05D2200/211 , F05D2250/25 , F05D2250/61 , F05D2260/205 , F16L51/028
摘要： A device comprises a bellows with protective rings arranged between corrugations of the bellows. Support rings are connected in a sealed manner to a gas line and a combustion chamber. A gimbal ring is positioned outside the bellows and via hinges is connected to structural brackets with support rings. A shield is mounted inside the bellows, the shield consisting of two cylindrical envelopes telescopically inserted one in another with a gap. The cylindrical envelopes are fixed in cantilever to support rings, forming a chamber which via channels for feeding a cooling working medium made in the support rings is connected to a main line for feeding the cooling working medium, and via the gap between the envelopes—to the cavity of the bellows unit. A housing is arranged outside the protective rings and adjoining them, and is made in the form of a metallic cylindrical helix, the ends of which are connected to the support rings (FIG. 2).
摘要翻译： 一种装置包括带有保护环的波纹管，其布置在波纹管的波纹之间。 支撑环以密封方式连接到气体管线和燃烧室。 万向节环位于波纹管外部，铰链通过支撑环连接到结构支架上。 屏蔽罩安装在波纹管内部，屏蔽层由两个圆柱形信封组成，两个圆柱形信封可伸缩地插入另一个间隙。 将圆柱形信封固定在支撑环上，形成一个室，通过用于供给在支撑环上制成的冷却工作介质的通道连接到用于供给冷却工作介质的主线，并且经由信封之间的间隙 波纹管单元的腔体。 一个外壳设置在保护圈的外面并与它们相邻，并且被制成一个金属圆柱形螺旋形的形式，其端部连接到支撑环（图2）。
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公开(公告)号：US12065989B2
公开(公告)日：2024-08-20
申请号：US17977292
申请日：2022-10-31
IPC分类号： B64C11/48 , F02K3/06 , B64C11/00 , B64C11/18 , F01D9/02 , F01D17/10 , F01D17/14 , F02C7/36 , F02K3/065 , F02K3/072 , F04D19/02 , F04D29/34 , F04D29/38
CPC分类号： F02K3/06 , B64C11/001 , B64C11/18 , B64C11/48 , F01D9/02 , F01D17/105 , F01D17/14 , F02C7/36 , F02K3/065 , F02K3/072 , F04D19/02 , F04D29/34 , F04D29/388 , F05D2200/14 , F05D2200/211 , F05D2220/323
摘要： A gas turbine is provided, the gas turbine engine including a turbomachine having an inlet splitter defining in part an inlet to a working gas flowpath and a fan duct splitter defining in part an inlet to a fan duct flowpath. The gas turbine engine also includes a primary fan driven by the turbomachine defining a primary fan tip radius R1, a primary fan hub radius R2, and a primary fan specific thrust rating TP; and a secondary fan downstream of the primary fan and driven by the turbomachine, the secondary fan defining a secondary fan tip radius R3, a secondary fan hub radius R4, and a secondary fan specific thrust rating TS; wherein the gas turbine engine defines an Effective Bypass Area, and wherein a ratio of R1 to R3 equals
R
1
R
3
=
(
EFP
)
(
1
-
RqR
(
Sec
.
-
Fan
)
2
)
(
1
-
RqR
Prim
.
-
Fan
2
)
(
T
P
T
S
)
(
EBA
)
.-
公开(公告)号：US11739699B2
公开(公告)日：2023-08-29
申请号：US17521352
申请日：2021-11-08
发明人： Martin Drolet , Yves Cloutier
CPC分类号： F02C9/22 , F02C9/18 , F02C9/20 , F05D2200/13 , F05D2200/14 , F05D2200/211 , F05D2220/323 , F05D2270/303 , F05D2270/3015 , F05D2270/3061 , F05D2270/335 , F05D2270/71
摘要： The method can include determining a mass flow rate W of working fluid circulating through the compressor stage, determining a control parameter value associated to the geometrical configuration of the variable geometry element based on the determined value of mass flow rate W; and changing the geometrical configuration of the variable geometry element in accordance with the determined control parameter value.
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公开(公告)号：US06851303B2
公开(公告)日：2005-02-08
申请号：US10334803
申请日：2003-01-02
CPC分类号： F01D25/285 , F01D21/003 , F05D2200/11 , F05D2200/211 , F05D2200/221 , G01L5/133
摘要： A method for determining the free-field thrust of a gas turbine engine using an enclosed gas turbine engine test facility without recourse to an outdoor gas turbine engine test facility. The method includes calculating the gas turbine engine intake momentum drag and cradle drag generated and compensating for these losses. In a further embodiment, the base drag is calculated and also compensated for.
摘要翻译： 一种用于使用封闭的燃气涡轮发动机测试设备来确定燃气涡轮发动机的自由场推力的方法，而不需要借助室外燃气涡轮发动机测试设备。 该方法包括计算产生的燃气涡轮发动机进气动量阻力和摇篮阻力并补偿这些损失。 在另一个实施例中，计算基础阻力并补偿。
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公开(公告)号：US4165949A
公开(公告)日：1979-08-28
申请号：US821863
申请日：1977-08-04
申请人： Gilbert Riollet
发明人： Gilbert Riollet
IPC分类号： F01D5/12 , F01D1/02 , F01D1/16 , F01D5/14 , H01J23/065 , H01J23/083 , H01J23/087 , H01J23/26 , H01J23/30 , H01J23/42 , H01J23/50 , H01J25/38 , H01P5/08 , H01Q11/08 , H03C3/30 , H03H2/00 , H04M5/04 , H04M19/02 , H04Q3/00 , F01D1/04 , F01D5/22 , F01D9/00
CPC分类号： H01J23/065 , F01D1/023 , F01D1/16 , F01D5/142 , H01J23/083 , H01J23/087 , H01J23/0876 , H01J23/26 , H01J23/30 , H01J23/42 , H01J23/50 , H01J25/38 , H01P5/08 , H01Q11/08 , H03C3/30 , H03H2/006 , H04M19/02 , H04M5/04 , H04Q3/00 , F05D2200/211 , Y10S415/914
摘要： In a turbine for a compressible fluid in which the fluid flow leaving the tepenultimate stage is separated into two coaxial flows, the inner flow passes through both the penultimate and the final stages of the turbine while the outer flow passes through the final stage only. This high efficiency arrangement for the last stages of a high power turbine exploits the advantages made available by using titanium as the blade material.
摘要翻译： 在用于可压缩流体的涡轮机中，其中离开过去阶段的流体流被分离成两个同轴流，当内部流仅通过最终级时，内部流动通过涡轮机的倒数第二级和最后级。 用于高功率涡轮机的最后阶段的这种高效率布置利用了使用钛作为叶片材料可获得的优点。
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公开(公告)号：US11859516B2
公开(公告)日：2024-01-02
申请号：US17896579
申请日：2022-08-26
发明人： David Marion Ostdiek
CPC分类号： F01D9/041 , F01D25/24 , F02C7/04 , F02K3/077 , F05D2200/12 , F05D2200/14 , F05D2200/211 , F05D2200/221 , F05D2240/128 , F05D2250/90 , F05D2260/213 , F05D2260/606
摘要： A gas turbine engine defining a centerline and a circumferential direction, the gas turbine engine including: a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order, the turbomachine defining a working gas flowpath and a fan duct flowpath; a primary fan driven by the turbomachine defining a primary fan tip radius R1 and a primary fan hub radius R2; a secondary fan located downstream of the primary fan and driven by the turbomachine, at least a portion of an airflow from the primary fan configured to bypass the secondary fan, the secondary fan defining a secondary fan tip radius R3 and a secondary fan hub radius R4, wherein the secondary fan is configured to provide a fan duct airflow through the fan duct flowpath during operation to generate a fan duct thrust, wherein the fan duct thrust is equal to % Fn3S of a total engine thrust during operation of the gas turbine engine at a rated speed during standard day operating conditions; wherein a ratio of R1 to R3 equals
(
EFP
)
(
1
-
R
q
R
Sec
.
-
Fan
2
)
(
1
-
R
q
R
Prim
.
-
Fa
n
2
)
(
1
%
Fn
3
S
-
1
)
;
wherein EFP is between 1.5 and 11, wherein RqRPrim.-Fan is a ratio of R1 to R2, and wherein RqRSec.-Fan is a ratio of R3 to R4.-
公开(公告)号：US20230258102A1
公开(公告)日：2023-08-17
申请号：US18138658
申请日：2023-04-24
发明人： Fangyuan Lou , Nicole Leanne Key
CPC分类号： F01D21/003 , F04D27/001 , G06F30/28 , F05D2220/32 , F05D2230/60 , F05D2200/11 , F05D2200/14 , F05D2200/211 , F05D2270/301 , F05D2270/803 , F05D2270/20 , F05D2200/30
摘要： A method of optimizing probe placement in a turbomachine is disclosed which includes establishing a design matrix A of size m×(2N+1) utilized in developing flow properties around an annulus of a turbomachine, where m represents the number of datapoints at different circumferential locations around the annulus, and N represents dominant wavelets generated by upstream and downstream stators and blade row interactions formed around an annulus, wherein m is greater or equal to 2N+1, and optimizing probe positioning by iteratively modifying probe positions placed around the annulus and for each iteration determining a condition number of the design matrix A for each set of probe positions until a predetermined threshold is achieved for the condition number representing an optimal probe layout.
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公开(公告)号：US07028378B2
公开(公告)日：2006-04-18
申请号：US09972863
申请日：2001-10-10
CPC分类号： B24C5/005 , B24B1/04 , B24B39/006 , B24C1/10 , B24C5/08 , F01D5/286 , F01D25/002 , F05D2200/211 , Y10T29/479 , Y10T29/49316 , Y10T29/49321
摘要： A part to be shot peened includes at least one thin wall (12″) defining two opposite main faces, the square root of the area of each face being greater than the mean distance between the two faces by a factor of at least five, and preferably by a factor of at least ten. According to the method, the part is caused to rotate at least intermittently relative to one or more vibrating surfaces, with at least one of the main faces being exposed to projectiles (6) set into motion by one or more of the vibrating surfaces, treatment taking place progressively on the face(s) so as to impart compression stresses thereto, with a portion only of the part being treated at any one time and with regions of the part preferably being exposed on several occasions to the projectiles, with relative rotation taking place between the exposures.
摘要翻译： 要喷丸硬化的部分包括限定两个相对的主面的至少一个薄壁（12“），每个面的面积的平方根大于两个面之间的平均距离至少五倍， 并且优选为至少十倍。 根据该方法，使部件相对于一个或多个振动表面至少间歇地旋转，其中至少一个主面暴露于通过一个或多个振动表面移动的射弹（6），处理 在表面上逐渐发生，以便赋予压缩应力，仅一部分被处理的部分在任何一个时间，并且该部分的区域优选地多次暴露于射弹，相对旋转 曝光之间的位置。
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