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1. 发明授权

US06557350B2 Method and apparatus for cooling gas turbine engine igniter tubes 有权
标题翻译：用于冷却燃气涡轮发动机点火器管的方法和装置
公开(公告)号：US06557350B2
公开(公告)日：2003-05-06
申请号：US09859611
申请日：2001-05-17
申请人： Gilbert Farmer , Ella Christine Kutter , Steven Clayton Vise , John Robert Staker , Marwan Al-Roub , Tariq Kay Harris
发明人： Gilbert Farmer , Ella Christine Kutter , Steven Clayton Vise , John Robert Staker , Marwan Al-Roub , Tariq Kay Harris
IPC分类号： F02C722
CPC分类号： F23R3/50 , F23R3/283 , F23R2900/00012 , F23R2900/03044
摘要： A combustor for a gas turbine engine includes a plurality of igniter tubes that facilitate reducing temperature gradients within the combustor in a cost effective and reliable manner. The combustor includes an annular outer liner that includes a plurality of openings sized to receive igniter tubes. Each igniter tube maintains an alignment of each igniter received therein, and includes an air impingement device that extends radially outward from the igniter tube. During operation, airflow contacting the air impingement device is channeled radially inward for impingement cooling of the igniter tubes and the combustor outer liner.
摘要翻译：用于燃气涡轮发动机的燃烧器包括多个点火器管，其以成本有效和可靠的方式有助于降低燃烧器内的温度梯度。燃烧器包括环形外衬套，其包括多个开口，其尺寸设置成接收点火器管。每个点火器管保持接收在其中的每个点火器的对准，并且包括从点火器管径向向外延伸的空气冲击装置。在操作期间，接触空气冲击装置的气流径向向内引导，用于点火器管和燃烧器外衬套的冲击冷却。

2. 发明授权

US06408629B1 Combustor liner having preferentially angled cooling holes 有权
标题翻译：燃烧器衬套具有优先倾斜的冷却孔
公开(公告)号：US06408629B1
公开(公告)日：2002-06-25
申请号：US09678069
申请日：2000-10-03
申请人： Tariq Kay Harris , Michael Burke Briski
发明人： Tariq Kay Harris , Michael Burke Briski
IPC分类号： F02C304
CPC分类号： F23R3/06 , Y02T50/675
摘要： Cooling film effectiveness is increased in multi-hole film cooled combustor liners having dilution holes by altering the orientation of the film cooling holes in the vicinity of the dilution holes. The cooling holes include a first group of cooling holes angled in a first circumferential direction and a second group of cooling holes angled in a second circumferential direction, opposite to the first circumferential direction. The cooling holes in the second group of cooling holes are located between adjacent ones of the dilution holes so as to direct cooling air to the regions immediately downstream of the dilution holes. Groups of oppositely directed cooling holes can be used with other hot spot regions on the liner, such as those caused by borescope holes, igniter ports and swirling combustor gases.
摘要翻译：通过改变稀释孔附近的薄膜冷却孔的取向，在具有稀释孔的多孔薄膜冷却的燃烧器衬套中提高了冷却膜效率。冷却孔包括在第一圆周方向上成角度的第一组冷却孔和与第一圆周方向相反的在第二圆周方向上成角度的第二组冷却孔。第二组冷却孔中的冷却孔位于相邻的稀释孔之间，以将冷却空气引导到紧邻稀释孔下游的区域。一组相反导向的冷却孔可以与衬套上的其它热点区域一起使用，例如由管道孔，点火器端口和旋转燃烧器气体引起的那些。

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