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1. 发明授权

US5743708A Turbine stator vane segments having combined air and steam cooling circuits 失效
标题翻译：具有组合的空气和蒸汽冷却回路的涡轮定子叶片段
公开(公告)号：US5743708A
公开(公告)日：1998-04-28
申请号：US674476
申请日：1996-07-02
申请人： Francisco J. Cunha , David A. DeAngelis , Theresa A. Brown , Sanjay Chopra , Victor H. S. Correia , Daniel R. Predmore
发明人： Francisco J. Cunha , David A. DeAngelis , Theresa A. Brown , Sanjay Chopra , Victor H. S. Correia , Daniel R. Predmore
IPC分类号： F01D9/02 , F01D5/18 , F01D9/04 , F01D11/00 , F02C7/16 , F01D9/06
CPC分类号： F01D5/189 , F01D11/005 , F01D5/187 , F01D5/188 , F05D2240/10 , F05D2240/81 , F05D2260/201 , F05D2260/2212 , F05D2260/2322 , Y02T50/67 , Y02T50/676
摘要： Turbine stator vane segments have inner and outer walls with vanes extending therebetween. The inner and outer walls are compartmentalized and have impingement plates. Steam flowing into the outer wall passes through the impingement plate for impingement cooling of the outer wall surface. The spent impingement steam flows into cavities of the vane having inserts for impingement cooling the walls of the vane. The steam passes into the inner wall and through the impingement plate for impingement cooling of the inner wall surface and for return through return cavities having inserts for impingement cooling of the vane surfaces. The trailing edge is air-cooled.
摘要翻译：涡轮机定子叶片段具有内壁和外壁，叶片间延伸有叶片。内壁和外壁分隔开并具有冲击板。流入外壁的蒸汽通过冲击板，用于冲击冷却外壁表面。废冲击蒸汽流入具有用于冲击冷却叶片壁的插入件的叶片的空腔中。蒸汽进入内壁并通过冲击板，用于内壁表面的冲击冷却，并通过具有用于叶片表面的冲击冷却的插入件的返回腔返回。后缘是风冷的。

2. 发明授权

US5634766A Turbine stator vane segments having combined air and steam cooling circuits 失效
标题翻译：具有组合的空气和蒸汽冷却回路的涡轮定子叶片段
公开(公告)号：US5634766A
公开(公告)日：1997-06-03
申请号：US414697
申请日：1995-03-31
申请人： Francisco J. Cunha , David A. DeAngelis , Theresa A. Brown , Sanjay Chopra , Victor H. S. Correia , Daniel R. Predmore
发明人： Francisco J. Cunha , David A. DeAngelis , Theresa A. Brown , Sanjay Chopra , Victor H. S. Correia , Daniel R. Predmore
IPC分类号： F01D9/02 , F01D5/18 , F01D9/04 , F01D11/00 , F02C7/16 , F01D9/06
CPC分类号： F01D5/189 , F01D11/005 , F01D5/187 , F01D5/188 , F05D2240/10 , F05D2240/81 , F05D2260/201 , F05D2260/2212 , F05D2260/2322 , Y02T50/67 , Y02T50/676
摘要： Turbine stator vane segments have inner and outer walls with vanes extending therebetween. The inner and outer walls are compartmentalized and have impingement plates. Steam flowing into the outer wall passes through the impingement plate for impingement cooling of the outer wall surface. The spent impingement steam flows into cavities of the vane having inserts for impingement cooling the walls of the vane. The steam passes into the inner wall and through the impingement plate for impingement cooling of the inner wall surface and for return through return cavities having inserts for impingement cooling of the vane surfaces. The trailing edge is air-cooled.
摘要翻译：涡轮机定子叶片段具有内壁和外壁，叶片间延伸有叶片。内壁和外壁分隔开并具有冲击板。流入外壁的蒸汽通过冲击板，用于冲击冷却外壁表面。废冲击蒸汽流入具有用于冲击冷却叶片壁的插入件的叶片的空腔中。蒸汽进入内壁并通过冲击板，用于内壁表面的冲击冷却，并通过具有用于叶片表面的冲击冷却的插入件的返回腔返回。后缘是风冷的。

3. 发明授权

US06394749B2 Apparatus and methods for relieving thermally induced stresses in inner and outer bands of thermally cooled turbine nozzle stages 失效
标题翻译：用于减轻热冷涡轮喷嘴级内外带热应力的装置和方法
公开(公告)号：US06394749B2
公开(公告)日：2002-05-28
申请号：US09761635
申请日：2001-01-18
申请人： Yufeng Phillip Yu , Gary Michael Itzel , Victor H. S. Correia
发明人： Yufeng Phillip Yu , Gary Michael Itzel , Victor H. S. Correia
IPC分类号： F01D906
CPC分类号： F01D25/10 , F01D5/187 , F01D11/24 , F01D25/08 , F01D25/12 , F05D2240/81
摘要： To control the temperature mismatch between the inner and outer bands and covers forming plenums with the inner and outer bands on sides thereof remote from the hot gas path, passages extend from the leading edge of the covers in communication with the hot gases of combustion to the trailing edge of the covers in communication with the hot gas flowpath. A mixing chamber is provided in each passage in communication with compressor discharge air for mixing the hot gases of combustion and compressor discharge air for flow through the passage, thereby heating the cover and minimizing the temperature differential between the inner and outer bands and their respective covers. The passages are particularly useful adjacent the welded or brazed joints between the covers and inner band portions.
摘要翻译：为了控制内带和外带之间的温度失配，并且覆盖形成集气室，其侧壁上的内带和外带远离热气路径，通道从盖的前缘延伸，与燃烧的热气体连通盖子的后缘与热气流路相通。在每个通道中设置有与压缩机排放空气连通的混合室，用于混合燃烧的热气体和压缩机排放空气以流过通道，从而加热盖并最小化内带和外带之间的温差及其各自的盖。这些通道在盖和内带部分之间的焊接或钎焊接头附近特别有用。

4. 发明授权

US06290459B1 Stationary flowpath components for gas turbine engines 失效
公开(公告)号：US06290459B1
公开(公告)日：2001-09-18
申请号：US09431462
申请日：1999-11-01
申请人： Victor H. S. Correia
发明人： Victor H. S. Correia
IPC分类号： F01D2526
CPC分类号： F01D11/008 , F01D5/143 , F01D9/04 , Y02T50/673
摘要： Cooling is facilitated in stationary flowpath components, such as turbine nozzle segments and shrouds, by providing circumferential edges defining a non-linear curvature that matches the curvature of the flow line defined by the gas flow past the stationary flowpath component. A flexible seal member is provided to accommodate the non-linear edges.

5. 发明授权

US5480281A Impingement cooling apparatus for turbine shrouds having ducts of increasing cross-sectional area in the direction of post-impingement cooling flow 失效
标题翻译：用于涡轮机护罩的冲击冷却装置，其具有在冲击后冷却流动方向上的横截面积增加的导管
公开(公告)号：US5480281A
公开(公告)日：1996-01-02
申请号：US269289
申请日：1994-06-30
申请人： Victor H. S. Correia
发明人： Victor H. S. Correia
IPC分类号： F01D11/08 , F01D25/12 , F01D25/14 , F01D25/26 , F01D9/02
CPC分类号： F01D25/12 , F01D11/08 , F05D2260/20 , F05D2260/201 , F05D2260/2322
摘要： A turbine shroud includes a plurality of cavities for receiving cooling steam for flow through the cavities in series counterflow to the direction of the hot gases of combustion. In the first cavity, a projection forms a nozzle to increase the velocity of the cooling steam to increase the convection coefficient for cooling the wall of the shroud. The steam flow in the second cavity passes through an impingement plate for impingement cooling of the wall of the shroud. Likewise, steam passes from the second cavity into the third cavity for flow through an impingement plate for further impingement cooling of the wall of the shroud. In the second and third cavities, the impingement plates include a plurality of ducts affording increased flow area in the direction of travel of the post-impingement steam flow to reduce cross-flow effects.
摘要翻译：涡轮机罩包括多个空腔，用于接收冷却蒸汽，用于流过通过空腔的串联逆流到燃烧热气体的方向。在第一腔中，突起形成喷嘴以增加冷却蒸汽的速度，以增加用于冷却护罩壁的对流系数。第二腔中的蒸汽流通过冲击板，用于对护罩的壁进行冲击冷却。同样地，蒸汽从第二腔体进入第三腔体，以流过冲击板，以进一步冲击冷却护罩壁。在第二和第三腔中，冲击板包括多个管道，其在后冲击蒸汽流的行进方向上提供增加的流动面积，以减少横流效应。

6. 发明授权

US06231307B1 Impingement cooled airfoil tip 失效
标题翻译：冲击冷却翼型尖端
公开(公告)号：US06231307B1
公开(公告)日：2001-05-15
申请号：US09323329
申请日：1999-06-01
申请人： Victor H. S. Correia
发明人： Victor H. S. Correia
IPC分类号： F01D518
CPC分类号： F01D5/187 , F01D5/186 , F01D5/20 , F05D2230/21 , F05D2260/202 , F05D2260/221 , Y02T50/676
摘要： A turbine airfoil includes pressure and suction sidewalls joined together at leading and trailing edges, and extending from root to tip. The tip includes a tip rib extending from a tip cap enclosing an internal flow channel between the sidewalls. An aligned pair of first and second holes extend through the tip cap and rib, respectively, for discharging coolant from the flow channel.
摘要翻译：涡轮机翼片包括在前缘和后缘处连接在一起的压力和抽吸侧壁，并且从根部延伸到尖端。尖端包括从封闭侧壁之间的内部流动通道的尖端盖延伸的尖端肋。对齐的一对第一和第二孔分别延伸穿过顶盖和肋，用于从流动通道排出冷却剂。

7. 发明授权

US5358374A Turbine nozzle backflow inhibitor 失效
标题翻译：涡轮喷嘴逆流抑制剂
公开(公告)号：US5358374A
公开(公告)日：1994-10-25
申请号：US94804
申请日：1993-07-21
申请人： Victor H. S. Correia , Richard W. Albrecht , Robert A. Frederick
发明人： Victor H. S. Correia , Richard W. Albrecht , Robert A. Frederick
IPC分类号： F01D5/08 , F01D5/18 , F02C7/18 , F01D9/06 , F01D11/00
CPC分类号： F02C7/18 , F01D5/081 , F01D5/187 , F05D2240/10 , Y02T50/676
摘要： A turbine nozzle includes a vane integrally joined between outer and inner bands, with the inner band having a purge hole for discharging a portion of cooling air channeled through the vane. A checkvalve is provided in the purge hole for preventing backflow therethrough into the vane. In an exemplary embodiment, the checkvalve allows a reduction in cooling air through the vane at low power operation for increasing efficiency while preventing backflow of combustion gases into the purge hole.
摘要翻译：涡轮喷嘴包括在外带和内带之间整体接合的叶片，内带具有用于排出通过叶片引导的冷却空气的一部分的吹扫孔。清洗孔中设有一个止回阀，用于防止通过其进入叶片的回流。在一个示例性实施例中，检查允许在低功率操作下减少通过叶片的冷却空气，以提高效率，同时防止燃烧气体回流到吹扫孔中。

8. 发明授权

US5332360A Stator vane having reinforced braze joint 失效
标题翻译：定子叶片加强钎焊接头
公开(公告)号：US5332360A
公开(公告)日：1994-07-26
申请号：US117853
申请日：1993-09-08
申请人： Victor H. S. Correia , Kevin G. McAllister
发明人： Victor H. S. Correia , Kevin G. McAllister
IPC分类号： F01D9/02 , F01D9/04
CPC分类号： F01D9/042 , F01D9/044 , Y10T29/49321
摘要： A gas turbine engine stator vane includes a groove extending laterally in an outer surface at one end thereof between leading and trailing edges for receiving a brazing material. The vane may be joined to an arcuate band having a complementary groove extending colinearly with the airfoil groove to collectively define therebetween an enlarged crevice for receiving the brazing material to form a reinforcing pin therein.
摘要翻译：燃气涡轮发动机定子叶片包括在其一端的外表面中横向延伸的槽，用于接收钎焊材料。叶片可以连接到具有与翼型槽共线延伸的互补槽的弓形带，以在其间共同限定用于接收钎焊材料以在其中形成加强销的扩大缝隙。

9. 发明授权

US5248240A Turbine stator vane assembly 失效
标题翻译：涡轮定子叶片总成
公开(公告)号：US5248240A
公开(公告)日：1993-09-28
申请号：US014908
申请日：1993-02-08
申请人： Victor H. S. Correia
发明人： Victor H. S. Correia
IPC分类号： F01D9/04
CPC分类号： F01D9/042
摘要： A three-piece stator vane assembly for use in gas turbine engines. The stator vane assembly is constructed so as to more readily withstand the mechanical stresses imposed during engine operation, as well as to reduce the tendency for the cast components of the stator vane assembly to recrystallize during the casting process, thus preserving the metallurgical integrity of the stator vane assembly. As a result, the stator vane assembly is better able to structurally withstand the severe operating conditions within the turbine section of a gas turbine engine.
摘要翻译：一种用于燃气涡轮发动机的三片式定子叶片组件。定子叶片组件被构造成更容易地承受在发动机运行期间施加的机械应力，并且降低定子叶片组件的铸造部件在铸造过程中再结晶的趋势，从而保持了铸造工艺中的冶金完整性定子叶片总成。因此，定子叶片组件更好地能够在结构上承受燃气涡轮发动机的涡轮部分内的严苛的操作条件。

10. 发明授权

US06413042B2 Stationary flowpath components for gas turbine engines 失效
标题翻译：燃气轮机的固定流路部件
公开(公告)号：US06413042B2
公开(公告)日：2002-07-02
申请号：US09828192
申请日：2001-04-09
申请人： Victor H. S. Correia
发明人： Victor H. S. Correia
IPC分类号： F01D2526
CPC分类号： F01D11/008 , F01D5/143 , F01D9/04 , Y02T50/673
摘要： Cooling is facilitated in stationary flowpath components, such as turbine nozzle segments and shrouds, by providing circumferential edges defining a non-linear curvature that matches the curvature of the flow line defined by the gas flow past the stationary flowpath component. A flexible seal member is provided to accommodate the non-linear edges.
摘要翻译：通过提供限定非线性曲率的周向边缘，使固定的流路部件（例如涡轮喷嘴段和护罩）有助于冷却，该非线性曲率与由气体流过固定流动路径部件所限定的流动线的曲率相匹配。提供柔性密封构件以容纳非线性边缘。

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