当前申请(专利权)人地址：
Kings Place, 90 York Way, London, N1 9FX , United Kingdom
摘要：
A fuel injector for a gas turbine engine (10 Fig. 1) has a feed arm (27 Fig. 2) and a nozzle (26 Fig. 2) which includes a pilot fuel discharge orifice and a mains fuel discharge orifice for respectively spraying pilot and mains fuel flows into a combustor (25 Fig. 2) of the engine. The nozzle and the feed arm contain one or more pilot passages 29 for flow of the pilot fuel flow from the pilot supply to the pilot discharge orifice and one or more mains passages 30 for flow of the mains fuel flow from the mains supply to the mains discharge orifice. The nozzle and the feed arm contain a plurality of the pilot passages and/or a plurality of the mains passages. The pilot and the mains passages intertwine repeatedly, and are both smoothly curved as they intertwine around each other. The pilot and mains passages may be coaxial, and the nozzle may be an air-spray nozzle formed by additive layer manufacture. The smoothly curved and intertwining passages make the fuel injector less susceptible to fuel coking.
权利要求：
CLAIMS
1. A fuel injector for a gas turbine engine, the injector having a nozzle including a pilot fuel discharge orifice and a mains fuel discharge orifice for respectively spraying pilot and mains fuel flows into a combustor of the engine, and further having a feed arm extending to the nozzle for feeding fuel to the pilot and mains discharge orifices from pilot and mains supplies respectively;
wherein the nozzle and the feed arm contain one or more pilot passages for flow of the pilot fuel flow from the pilot supply to the pilot discharge orifice and one or more mains passages for flow of the mains fuel flow from the mains supply to the mains discharge orifice;
wherein the nozzle and the feed arm contain a plurality of the pilot passages and/or a plurality of the mains passages; and
wherein the pilot and the mains passages intertwine repeatedly , and are both smoothly curved as they intertwine around each other.
2. A fuel spray nozzle according to claim 1, wherein the pilot and the mains passages intertwine in the nozzle and/or the feed arm.
3. A fuel spray nozzle according to claim 1 or 2, wherein the pilot fuel discharge orifice and the mains fuel discharge orifice are coaxial.
4. A fuel spray nozzle according to claim 3, wherein the pilot fuel discharge orifice is radially inwards of the mains fuel discharge orifice.
5. A fuel spray nozzle according to any one of the previous claims, wherein the nozzle is an airspray nozzle, the nozzle having one or more air circuits for directing discharge air from a compressor of the engine to the pilot and the mains discharge orifices, thereby atomising the fuel flows sprayed by the discharge orifices.
6. A fuel spray nozzle according to any one of the previous claims, wherein the pilot and the mains passages are formed by additive layer manufacture.
7. A combustor for a gas turbine engine having a plurality of fuel injectors according to any one of the previous claims.
8. A gas turbine engine having a combustor according to claim 7.
9. A method of forming a fuel injector according to any one of claims 1 to 5, the me including forming the pilot and the mains passages by additive layer manufacture.