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1. 发明授权

US5181377A Damped combustor cowl structure 失效
标题翻译：阻燃的COMBUSTOR COWL结构
公开(公告)号：US5181377A
公开(公告)日：1993-01-26
申请号：US685947
申请日：1991-04-16
申请人： Phillip D. Napoli , John M. Koshoffer
发明人： Phillip D. Napoli , John M. Koshoffer
IPC分类号： F23R3/42 , F23R3/00 , F23R3/60
CPC分类号： F23R3/60 , F23R3/002
摘要： A friction-damped combustor cowl is formed of first and second plies of sheet material of mating, generally annular configuration defining a central cowl axis and of axially elongated and aerodynamically contoured configuration have respective fore end portions which are curled to form a cowl leading edge of arcuate cross section and corresponding fore edges which are integrally joined, and respective aft end portions which define a cowl trailing edge and corresponding aft edges which are integrally joined. Surface contact of the contiguous surfaces of the laminated and mating first and second plies provides vibration damping under normal operating conditions in an alternative and combustor cowl, a spring element is received and maintained under compression within the curled leading edge of the combustor cowl and maintains a resilient biasing force maintaining surface contact between the spring element and the interior surface of the curled leading edge, thereby maintaining frictional surface contact and requisite vibration damping under normal operating conditions.

2. 发明授权

US06571559B1 Anti-carboning fuel-air mixer for a gas turbine engine combustor 失效
标题翻译：用于燃气涡轮发动机燃烧器的抗燃燃料空气混合器
公开(公告)号：US06571559B1
公开(公告)日：2003-06-03
申请号：US09054794
申请日：1998-04-03
申请人： Douglas M. Fortuna , William T. Houchens , Gary L. Leonard , Phillip D. Napoli , Paul E. Sabla , Douglas G. Shafer , Jack W. Smith, Jr.
发明人： Douglas M. Fortuna , William T. Houchens , Gary L. Leonard , Phillip D. Napoli , Paul E. Sabla , Douglas G. Shafer , Jack W. Smith, Jr.
IPC分类号： F02C722
CPC分类号： F23D11/103 , F02C7/22 , F23D2209/30 , F23D2900/00016 , F23R3/28
摘要： A fuel-air mixer for a gas turbine engine combustor having a primary swirler and a venturi that effectively reduces carboning via purge air. Purge air flows axially through the fuel-air mixer forming a boundary layer of air on the inner surface of the venturi. The boundary layer of air minimizes the amount of fuel contacting the inner surface of the venturi resulting in reduced carbon resin or coke formation.
摘要翻译：一种用于具有初级旋流器和文氏管的燃气涡轮发动机燃烧器的燃料空气混合器，其有效地通过吹扫空气来减少碳化。吹扫空气轴向流动通过燃料 - 空气混合器，在文丘里管的内表面上形成边界层的空气。空气的边界层使与文氏管内表面接触的燃料量最小化，导致碳树脂或焦炭形成减少。

3. 发明授权

US5321949A Staged fuel delivery system with secondary distribution valve 失效
标题翻译：具有二次分配阀的分段燃油输送系统
公开(公告)号：US5321949A
公开(公告)日：1994-06-21
申请号：US729238
申请日：1991-07-12
申请人： Phillip D. Napoli , Thomas C. Campbell
发明人： Phillip D. Napoli , Thomas C. Campbell
IPC分类号： F02C9/28 , F02C7/228 , F02C9/34 , F02L1/00
CPC分类号： F02C9/34 , F02C7/228
摘要： A fuel delivery system for a turbine engine having a primary fuel flow circuit and a secondary fuel flow circuit. The primary fuel flow circuit has a unstaged-first manifold and a staged-second manifold. A control valve and flow meter regulate the amount of fuel flow to the unstaged and staged manifolds with a first mode of operation providing fuel to the unstaged manifold only, and a second mode of operation providing fuel to both the staged and unstaged manifolds. When high power is required of the engine, a secondary fuel circuit is provided with a secondary manifold which is connected to a distribution valve which opens when fuel flow is at a predetermined level. The invention allows fuel to be efficiently atomized at various levels of powered operation by having a control center which controls the opening and closing of the distribution valve and control valve based upon fuel flow rates fuel/air ratios and air start core speed.
摘要翻译：一种用于涡轮发动机的燃料输送系统，其具有主要燃料流动回路和二次燃料流动回路。主要燃料流动回路具有未分级第一歧管和分级第二歧管。控制阀和流量计通过第一操作模式来调节到未分级和分级歧管的燃料流量，仅将燃料提供给未分级歧管，以及将第二操作模式向分阶段和未分级歧管提供燃料。当需要发动机的高功率时，辅助燃料回路设置有二次歧管，该二次歧管连接到当燃料流量处于预定水平时打开的分配阀。本发明通过具有基于燃料流量燃料/空气比和空气启动核心速度来控制分配阀和控制阀的打开和关闭的控制中心，可以在各种动力操作水平下有效地雾化燃料。

4. 发明授权

US5279127A Multi-hole film cooled combustor liner with slotted film starter 失效
标题翻译：多孔薄膜燃烧器衬套，带开槽薄膜起动器
公开(公告)号：US5279127A
公开(公告)日：1994-01-18
申请号：US941770
申请日：1992-09-04
申请人： Phillip D. Napoli
发明人： Phillip D. Napoli
IPC分类号： F02K1/82 , F23R3/00 , F23R3/06
CPC分类号： F02K1/822 , F23R3/002 , F23R3/06 , F05D2260/202 , F23R2900/00005 , Y02T50/67 , Y02T50/671 , Y02T50/676
摘要： A gas turbine engine combustor is provided with a combustor liner film cooling means having a slotted nugget or ring for starting a cooling film on and upstream of a multi-hole single wall sheet metal combustor liner which is generally annular in shape and having disposed therethrough a multi-hole film cooling means which includes at least one pattern of small closely spaced film cooling holes sharply angled in the downstream direction. In one embodiment the cooling holes are angled in a circumferential direction which generally coincides with the swirl angle of the flow along the surface of the liner. Another embodiment provides a that the annular liner is corrugated so as to form an axially extending wavy wall to help resist buckling which is particularly useful for outer liners in the combustion section of aircraft gas turbine engines and in the exhaust section of gas turbine engines and afterburners.
摘要翻译：燃气涡轮发动机燃烧器设置有燃烧器衬套膜冷却装置，该燃烧器衬套膜冷却装置具有开槽的熔核或环，用于在多孔单壁金属板燃烧器衬套上和上游起动一个冷却膜，所述多孔单壁金属板燃烧器衬套通常是环形的并且穿过其设置多孔膜冷却装置，其包括在下游方向上锐度成角度的小的紧密间隔的薄膜冷却孔的至少一个图案。在一个实施例中，冷却孔在圆周方向成角度，该圆周方向大致与沿着衬套表面的流动的旋转角度重合。另一个实施例提供了一种环形衬套是波纹形的，以便形成轴向延伸的波浪壁，以帮助抵抗对于飞机燃气涡轮发动机的燃烧部分和燃气涡轮发动机和后燃烧器的排气部分中的外衬层特别有用的弯曲。

5. 发明授权

US5257502A Fuel delivery system for dual annular combustor 失效
标题翻译：双环形燃烧器燃油输送系统
公开(公告)号：US5257502A
公开(公告)日：1993-11-02
申请号：US993483
申请日：1992-12-18
申请人： Phillip D. Napoli
发明人： Phillip D. Napoli
IPC分类号： F02C7/228 , F02C9/34 , F23R3/34 , F02C7/22
CPC分类号： F02C9/34 , F02C7/228 , F23R3/34 , F05D2270/31
摘要： A fuel delivery system for a dual annular combustor having a pilot stage manifold, a first main stage manifold, and a second main stage manifold which are connected to a three-position staging valve. The staging valve is controlled by a fuel/air digital electronic control (FADEC) which directs the staging valve to a closed (staged) position, to a partially open (partially staged) position, or to an open (unstaged) position in accordance with a staging-valve-fuel-to-air-ratio control schedule.
摘要翻译：一种用于双环形燃烧器的燃料输送系统，其具有连接到三位分级阀的先导级歧管，第一主级歧管和第二主级歧管。分级阀由燃料/空气数字电子控制器（FADEC）控制，该控制器将分段阀定向到关闭（分级）位置，部分打开（部分分级）位置或打开（未打开）位置，根据分段阀 - 燃料空气比控制计划。

6. 发明授权

US5233828A Combustor liner with circumferentially angled film cooling holes 失效
标题翻译：具有周向成角度的薄膜冷却孔的燃烧器衬套
公开(公告)号：US5233828A
公开(公告)日：1993-08-10
申请号：US951025
申请日：1992-09-24
申请人： Phillip D. Napoli
发明人： Phillip D. Napoli
IPC分类号： F02K1/82 , F23R3/00
CPC分类号： F23R3/002 , F02K1/822 , F05D2260/202 , F23R2900/00005 , Y02T50/67 , Y02T50/671 , Y02T50/676
摘要： A gas turbine engine combustor is provided, having a an annular single wall sheet metal liner which is generally annular in shape and having disposed therethrough a multi-hole film cooling means which includes at least one pattern of small closely spaced film cooling holes angled sharply in the downstream direction and angled in a circumferential direction wherein the circumferential angle generally coincides with the swirl angle of the flow along the surface of the liner. Another embodiment provides a corrugated aircraft engine sheet metal combustor liner which forms an axially extending wavy wall to help resist buckling, particularly useful for outer liners in the combustion section of the engine and in the exhaust section of gas turbine engines incorporating afterburners.
摘要翻译：提供了一种燃气涡轮发动机燃烧器，其具有环形单壁金属衬垫，该环形单壁金属衬垫通常为环形，并且穿过其设置有多孔膜冷却装置，该多孔膜冷却装置包括至少一个小的紧密间隔的薄膜冷却孔的图案，下游方向并且在圆周方向上成角度，其中圆周角度通常与沿着衬套的表面的流动的旋转角度重合。另一实施例提供了一种波纹飞机发动机钣金燃烧器衬套，其形成轴向延伸的波浪壁以帮助抵抗弯曲，特别适用于发动机的燃烧部分和装有后燃烧器的燃气涡轮发动机的排气部分中的外衬。

7. 发明授权

US5924288A One-piece combustor cowl 失效
标题翻译：单件式燃烧器整流罩
公开(公告)号：US5924288A
公开(公告)日：1999-07-20
申请号：US811754
申请日：1997-03-06
申请人： Douglas M. Fortuna , Phillip D. Napoli , Richard A. Duke
发明人： Douglas M. Fortuna , Phillip D. Napoli , Richard A. Duke
IPC分类号： F23R3/00 , F02C1/00
CPC分类号： F23R3/002
摘要： A one-piece cowl is provided for use in assembled relationship with a combustor of a gas turbine engine. The cowl is of a generally annular configuration which defines a central cowl axis, and is axially elongated and aerodynamically contoured relative to the central cowl axis. In order to provide a vibratory damping function for the cowl, a solid lip of increased thickness is formed at a leading edge of the cowl.
摘要翻译：提供一体式整流罩用于与燃气涡轮发动机的燃烧器组装关系。整流罩具有大致环形的构造，其限定中央整流罩轴线，并且相对于中央整流罩轴线轴向伸长并且具有空气动力学轮廓。为了提供整流罩的振动阻尼功能，在整流罩的前缘形成增加厚度的固体唇缘。

8. 发明授权

US5261222A Fuel delivery method for dual annular combuster 失效
标题翻译：双环形燃烧器燃油输送方式
公开(公告)号：US5261222A
公开(公告)日：1993-11-16
申请号：US982366
申请日：1992-11-27
申请人： Phillip D. Napoli
发明人： Phillip D. Napoli
IPC分类号： F02C7/228 , F02C9/34 , F23R3/34
CPC分类号： F23R3/34 , F02C7/228 , F02C9/34 , F05D2270/31
摘要： A fuel delivery system for a dual annular combustor having a pilot stage manifold, a first main stage manifold, and a second main stage manifold which are connected to a three-position staging valve. The staging valve is controlled by a fuel/air digital electronic control (FADEC) which directs the staging valve to a closed (staged) position, to a partially open (partially staged) position, or to an open (unstaged) position in accordance with a staging-valve-fuel-to-air-ratio control schedule.
摘要翻译：一种用于双环形燃烧器的燃料输送系统，其具有连接到三位分级阀的先导级歧管，第一主级歧管和第二主级歧管。分级阀由燃料/空气数字电子控制器（FADEC）控制，该控制器将分段阀定向到关闭（分级）位置，部分打开（部分分级）位置或打开（未打开）位置，根据分段阀 - 燃料空气比控制计划。

9. 发明授权

US5106203A Exhaust gas temperature sensor 失效
标题翻译：废气温度传感器
公开(公告)号：US5106203A
公开(公告)日：1992-04-21
申请号：US562358
申请日：1990-08-03
申请人： Phillip D. Napoli , Francis P. Laska
发明人： Phillip D. Napoli , Francis P. Laska
IPC分类号： F01D17/08 , G01K3/14 , G01K13/02
CPC分类号： G01K3/14 , F01D17/085 , G01K13/02 , Y02T50/671
摘要： An exhaust gas temperature sensor is described which includes first, second and third thermocouples connected in parallel to measure the gas temperature at the first, second and third penetration depths in an exhaust passage. In a preferred embodiment of the present invention, an exhaust temperature sensor mounted in a turbine passage including an inner and outer wall includes a first thermocouple located between approximately 26 percent and 30 percent of the distance from the outer wall to the inner wall. A second thermocouple is located between approximately 58 percent and 62 percent of the distance between the outer and inner passage walls. A third thermocouple is located between approximately 68 percent and 72 percent of the distance between the inner and outer passage walls.
摘要翻译：描述了一种排气温度传感器，其包括并联连接的第一，第二和第三热电偶，以测量排气通道中第一，第二和第三穿透深度处的气体温度。在本发明的优选实施例中，安装在包括内壁和外壁的涡轮通道中的排气温度传感器包括位于从外壁到内壁的距离的约26％至30％之间的第一热电偶。第二热电偶位于外通道壁和内通道壁之间的距离的约58％和62％之间。第三个热电偶位于内部和外部通道壁之间的距离的大约68％和72％之间。

10. 发明授权

US4554789A Seal cooling apparatus 失效
标题翻译：密封冷却装置
公开(公告)号：US4554789A
公开(公告)日：1985-11-26
申请号：US594956
申请日：1984-04-02
申请人： Phillip D. Napoli , William R. Patterson
发明人： Phillip D. Napoli , William R. Patterson
IPC分类号： F01D11/04 , F01D25/12
CPC分类号： F01D11/04
摘要： An improved seal cooling apparatus is provided for use in a gas turbine engine. In a particular embodiment, this apparatus includes means for deriving conditioning air from air discharged from the compressor diffuser and directing this air onto the seal stator to improve its thermal response. The apparatus also includes means to inject a portion of the conditioning air into a cavity forward of the seal to purge the region and prevent zero airflow conditions during engine operation for the purpose of discouraging overheating of a portion of the compressor rotor. A portion of the conditioning air from the cavity is subsequently directed to flow through and thereby cool the seal.
摘要翻译：提供了一种用于燃气涡轮发动机的改进的密封冷却装置。在特定实施例中，该装置包括用于从空气压缩机扩散器排出的空气中调节空气的调节装置，并将该空气引导到密封定子上以改善其热响应。该装置还包括将调节空气的一部分注入到密封件前方的空腔以清除该区域并防止在发动机运行期间的零气流状况以减少压缩机转子的一部分过热的装置的装置。随后将来自空腔的调节空气的一部分导向流过，从而冷却密封。

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