OUTER PREMIX BARREL VENT AIR SWEEP
First Claim
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1. An outer premix barrel for a fuel injector of a gas turbine engine, comprising:
- a body portion includingvent air inlets;
a barrel portion extending axially aft from the body portion; and
a plurality of vanes extending axially forward from the body portion, each vane includingan inward surface located at a radially inner end of the vane, anda plurality of vent passages exiting the vane at the inward surface, each vent passage being in flow communication with at least one vent air inlet.
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Abstract
A gas turbine engine outer premix barrel is disclosed. The outer premix barrel includes a body portion, a barrel portion, and a plurality of vanes. The body portion includes vent air inlets. The barrel portion extends axially aft from the body portion. The plurality of vanes extends axially forward from the body portion. Each vane includes an inward surface located at a radially inner end of the vane, and a plurality of vent passages exiting the vane at the inward surface. Each vent passage is in flow communication with at least one vent air inlet.
4 Citations
20 Claims
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1. An outer premix barrel for a fuel injector of a gas turbine engine, comprising:
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a body portion including vent air inlets; a barrel portion extending axially aft from the body portion; and a plurality of vanes extending axially forward from the body portion, each vane including an inward surface located at a radially inner end of the vane, and a plurality of vent passages exiting the vane at the inward surface, each vent passage being in flow communication with at least one vent air inlet. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10)
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11. A gas turbine engine outer premix barrel, comprising:
a barrel including a body portion with an annular disk shape, the body portion including vent air inlets extending axially through the annular disk shape, a barrel portion extending axially aft from an aft and radially inner portion of the body portion, and a plurality of vanes extending from the body portion opposite the barrel portion, each vane including an inward surface located at an end of the vane and is a radially inner surface of the vane, and a plurality of vent passages in flow communication with at least one vent air inlet, each vent passage exiting the vane at the inward surface. - View Dependent Claims (12, 13, 14, 15, 16)
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17. A method for overhauling a gas turbine engine injector, comprising:
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removing an outer premix barrel from the injector, the outer premix barrel including a barrel including a body portion including vent air inlets, a barrel portion extending axially aft from the body portion, and a plurality of vanes extending axially forward from the body portion, each vane including a truncated wedge shape and a plurality of vent passages in flow communication with at least one vent air inlet, each vent passage exits the vane at an inward surface located at a truncated portion of the truncated wedge shape, and a barrel end joined to the barrel at an aft end of the barrel portion, the barrel end including a cylindrical tube shape; separating the barrel end from the barrel; joining a new barrel end to the barrel with a metal joining process. - View Dependent Claims (18, 19, 20)
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Specification