-
1.发明申请公开(公告)号：US20130269360A1
公开(公告)日：2013-10-17
申请号：US13444918
申请日：2012-04-12
Applicant: Lisa Anne Wichmann , Jeffrey John Butkiewicz , Stanley Frank Simpson
Inventor： Lisa Anne Wichmann , Jeffrey John Butkiewicz , Stanley Frank Simpson
CPC classification number: F02C6/18 , F02C3/107 , F02C9/00 , F05D2220/72 , Y02E20/16
Abstract: The present invention provides a system and method of operating a combined-cycle powerplant at part-load without shutting down an HRSG and steam turbine. The present invention may apply to a powerplant operating in an open-cycle mode. The present invention may also apply to a powerplant operating in a closed-cycle mode.
Abstract translation: 本发明提供了一种在部分负载下操作组合循环动力装置而不关闭HRSG和蒸汽轮机的系统和方法。 本发明可以应用于以开环模式操作的动力装置。 本发明还可以应用于以闭环模式操作的动力装置。
-
公开(公告)号：US20110038708A1
公开(公告)日：2011-02-17
申请号：US12538923
申请日：2009-08-11
Applicant: Jeffrey John Butkiewicz
Inventor： Jeffrey John Butkiewicz
CPC classification number: F01D5/186 , F05D2260/202 , Y10T29/49341
Abstract: An airfoil is provided and includes an airfoil body having a pressure surface extendable between radial ends and a fluid path in an airfoil interior defined therein. The pressure surface is formed to further define a passage by which coolant is deliverable from the fluid path in the airfoil interior, in a perimetric direction from the pressure surface for the purpose of cooling a portion on the surface of the radial end.
Abstract translation: 提供了翼型件，并且包括翼型件主体，其具有在径向端部之间延伸的压力表面和在其中限定的翼型件内部中的流体路径。 形成压力表面以进一步限定通道，通过该通道，冷却剂可以从翼型件内部的流体路径以压力表面的周边方向输送，以便冷却径向端的表面上的部分。
-
公开(公告)号：US20090074589A1
公开(公告)日：2009-03-19
申请号：US11856945
申请日：2007-09-18
Applicant: Biao Fang , Christopher Edward Wolfe , Omprakash Samudrala , Matthew Scott Kight , Jeffrey John Butkiewicz , Tara McGovern
Inventor： Biao Fang , Christopher Edward Wolfe , Omprakash Samudrala , Matthew Scott Kight , Jeffrey John Butkiewicz , Tara McGovern
IPC: F01D5/08
Abstract: In a gas turbine having a compressor discharge casing, a cooling circuit diverts compressor discharge air toward a high pressure packing (HPP) circuit. The cooling circuit includes an inlet pipe that receives compressor discharge air. One or several cooled cooling air pipes are in fluid communication with the inlet pipe via a pipe manifold, which distributes the discharge air across the cooled cooling air pipes. A seal is disposed upstream of an entrance to the HPP circuit to limit flow into the HPP circuit, and a second seal is disposed downstream of the HPP circuit at turbine wheelspace to limit ingestion and thus the purge flow air required. The circuit serves to reduce required purge flow in the HPP circuit so that an amount of compressor discharge air can be put back to the main flow path, thereby improving turbine performance.
Abstract translation: 在具有压缩机排放壳体的燃气轮机中，冷却回路将压缩机排出的空气转向高压包装（HPP）回路。 冷却回路包括接收压缩机排出空气的入口管。 一个或几个冷却的冷却空气管通过管道歧管与入口管流体连通，管道歧管将排放空气分配在冷却的冷却空气管道上。 密封件设置在HPP回路入口的上游，以限制流入HPP回路的第二密封件，并且在涡轮机轮距处设置在HPP回路下游的第二密封件，以限制摄入量，从而限制吸入流量所需的空气流量。 该电路用于减少HPP电路中所需的清洗流量，使得压缩机排出空气的量可以放回到主流路，从而提高涡轮机性能。
-
4.发明申请Heading reference command and control algorithm and cueing systems and methods for aircraft turn-to-target maneuvers 有权飞行器到目标机动的标题参考命令和控制算法以及提示系统和方法公开(公告)号：US20070030174A1
公开(公告)日：2007-02-08
申请号：US11198630
申请日：2005-08-05
Applicant: Pasquale Randazzo , John Butkiewicz , David Miller , David Mossman , Paul Redkoles , Channing Morse
Inventor： Pasquale Randazzo , John Butkiewicz , David Miller , David Mossman , Paul Redkoles , Channing Morse
IPC: G01C21/00
CPC classification number: G01C23/005 , G05D1/0858
Abstract: Systems and methods are provided for determining a final heading of a turning vehicle, such as a rotorcraft. The system may include an algorithm that calculates an advance prediction of a final heading that will be achieved after control input is terminated. The system may also include a device, such as a display, for conveying predicted final heading information to an aircraft controller, such as a pilot.
Abstract translation: 提供了用于确定诸如旋翼航空器的转向车辆的最终航向的系统和方法。 系统可以包括计算在控制输入终止之后将实现的最终航向的提前预测的算法。 系统还可以包括诸如显示器的装置，用于将预测的最终航向信息传送到诸如飞行员的飞行器控制器。
-
公开(公告)号：US06527274B2
公开(公告)日：2003-03-04
申请号：US09736118
申请日：2000-12-13
Applicant: William Lee Herron , Jeffrey John Butkiewicz
Inventor： William Lee Herron , Jeffrey John Butkiewicz
IPC: F16J1544
CPC classification number: F16J15/3292
Abstract: A seal assembly for installation between rotating and stationary components of a machine includes a first plurality of leaf spring segments secured to the stationary component in a circumferential array surrounding the rotating component, the leaf spring segments each having a radial mounting portion and a substantially axial sealing portion, the plurality of leaf spring segments shingled in a circumferential direction.
-
Patent Agency Ranking
公开(公告)号：US06234746B1
公开(公告)日：2001-05-22
申请号：US09368121
申请日：1999-08-04
Applicant: Mark Stewart Schroder , Jeffrey John Butkiewicz
Inventor： Mark Stewart Schroder , Jeffrey John Butkiewicz
IPC: F01D508
Abstract: A cooling system for turbomachinery includes a compressor bleed air passageway for supplying bleed cooling air to a plurality of circumferentially spaced, generally axially extending passages in communication with a cavity within the inner barrel in which the flanges of the turbine and compressor rotors are secured to one another. The exit ends of the passages have swirl devices for turning the flow from the general axial direction to a tangential direction corresponding to the direction of rotation of the combined rotors. A leakage seal is provided between the rotor and the stationary component to provide a pressure drop across a plenum and cavity to increase the velocity of air flowing into the cavity. Consequently, cooling air is supplied the cavity at a tangential velocity approaching the rotor velocity with reduced windage and lower temperature, thereby improving the performance of the turbomachinery.
Abstract translation: 用于涡轮机械的冷却系统包括压缩机排放空气通道，用于向多个周向间隔开的大致轴向延伸的通道提供排放冷却空气，该通道与内筒内的空腔连通，涡轮机和压缩机转子的凸缘固定在其中 另一个。 通道的出口端具有用于将流体从总体轴向方向转向对应于组合转子的旋转方向的切线方向的旋流装置。 在转子和固定部件之间提供泄漏密封件，以在压力通风室和空腔之间提供压降，以增加流入空腔的空气的速度。 因此，冷却空气以降低的风阻和较低的温度以接近于转子速度的切向速度供应空腔，从而改善涡轮机械的性能。
-
公开(公告)号：US08727726B2
公开(公告)日：2014-05-20
申请号：US12538923
申请日：2009-08-11
Applicant: Jeffrey John Butkiewicz
Inventor： Jeffrey John Butkiewicz
IPC: F01D25/12
CPC classification number: F01D5/186 , F05D2260/202 , Y10T29/49341
Abstract: An airfoil is provided and includes an airfoil body having a pressure surface extendable between radial ends and a fluid path in an airfoil interior defined therein. The pressure surface is formed to further define a passage by which coolant is deliverable from the fluid path in the airfoil interior, in a perimetric direction from the pressure surface for the purpose of cooling a portion on the surface of the radial end.
Abstract translation: 提供了翼型件，并且包括翼型件主体，其具有在径向端部之间延伸的压力表面和在其中限定的翼型件内部中的流体路径。 形成压力表面以进一步限定通道，通过该通道，冷却剂可以从翼型件内部的流体路径以压力表面的周边方向输送，以便冷却径向端的表面上的部分。
-
8.发明申请METHOD AND SYSTEM FOR CONTROLLING A STOICHIOMETRIC EGR SYSTEM ON A REGENERATIVE REHEAT SYSTEM 审中-公开再生再循环系统控制系统的方法与系统公开(公告)号：US20130269356A1
公开(公告)日：2013-10-17
申请号：US13444929
申请日：2012-04-12
Applicant: Jeffrey John Butkiewicz , Stanley Frank Simpson , Lisa Anne Wichmann
Inventor： Jeffrey John Butkiewicz , Stanley Frank Simpson , Lisa Anne Wichmann
IPC: F02C6/06
Abstract: Embodiments of the present invention provide a S-EGR process that yields an exhaust stream that includes a relatively high concentration of a desirable gas and is also substantially oxygen-free. This desirable gas includes, but is not limited to: Carbon Dioxide (CO2), Nitrogen (N2), or Argon.
Abstract translation: 本发明的实施方案提供了一种S-EGR方法，其产生包含相对高浓度的期望气体并且也基本上不含氧的排气流。 这种期望的气体包括但不限于：二氧化碳（CO 2），氮气（N 2）或氩气。
-
9.发明申请Heading reference command and control algorithm systems and methods for aircraft turn-to-target maneuvers 有权飞行器到目标机动的标题参考命令和控制算法系统和方法公开(公告)号：US20070032923A1
公开(公告)日：2007-02-08
申请号：US11197977
申请日：2005-08-05
Applicant: David Mossman , John Butkiewicz
Inventor： David Mossman , John Butkiewicz
IPC: G06F17/00
CPC classification number: G05D1/0858
Abstract: Systems and methods are provided for determining a final heading of a turning vehicle, such as a rotorcraft. The system may include an algorithm that calculates an advance prediction of a final heading that will be achieved after control input is terminated.
Abstract translation: 提供了用于确定诸如旋翼航空器的转向车辆的最终航向的系统和方法。 系统可以包括计算在控制输入终止之后将实现的最终航向的提前预测的算法。
-
公开(公告)号：US08734107B2
公开(公告)日：2014-05-27
申请号：US13149426
申请日：2011-05-31
Applicant: Jeffrey John Butkiewicz , Stanley Frank Simpson
Inventor： Jeffrey John Butkiewicz , Stanley Frank Simpson
IPC: F01D5/20
CPC classification number: F01D5/147 , F01D5/20 , F01D5/282 , F01D5/284 , F05D2300/6033
Abstract: A turbine bucket may generally include an airfoil formed from a metal-based material. The airfoil may include a base and a tip disposed opposite the base. The airfoil may also include a pressure side wall and a suction side wall extending between a leading edge and a trailing edge. Additionally, the turbine bucket may include a tip cap disposed between the pressure side wall and the suction side wall. The tip cap may be formed from a ceramic matrix composite material.
Abstract translation: 涡轮机桶通常可以包括由金属基材料形成的翼型件。 翼型件可以包括基部和与基部相对设置的尖端。 翼型件还可以包括在前缘和后缘之间延伸的压力侧壁和吸力侧壁。 此外，涡轮机桶可以包括设置在压力侧壁和吸力侧壁之间的末端盖。 尖端帽可以由陶瓷基复合材料形成。
-
-
-
-
-
-
-
-
-
Search Results
20
records
(took 0.014 seconds)
