A cold air buffer supply tube for a gas turbine engine includes a tube body having a first tube end and a second tube end. A fitting is secured to the first tube end, and a metering cap is secured to the tube second end. The metering cap includes a cap body having a peripheral wall with a plurality of holes to direct flow from an air supply into a bearing compartment for the gas turbine engine.
1. A cold air buffer supply tube for a gas turbine engine comprising: a tube body having a first tube end and a second tube end;a fitting secured to said first tube end;a metering cap secured to said second tube end, said metering cap having a cap body with a peripheral wall that includes a plurality of holes to direct flow into a bearing compartment for the gas turbine engine. 2. The cold air buffer supply tube according to claim 1 wherein said cap body comprises a cup-shaped body having a distal end face and an open end that is in fluid communication w...
이 특허에 인용된 특허 (10)
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- Coffin, James B.; Davis, Todd A.; DiBenedetto, Enzo. Forward compartment service system for a geared architecture gas turbine engine. USP2016089410447.
- Grogg, Gary L; Szymanski, Grace E. Heatshield discourager seal for a gas turbine engine. USP2018019856746.