1. A method for assembling a gas turbine engine, said method comprising:
coupling a first fuel system interface (FSI-1) to a second fuel system interface (FSI-2);
coupling one of the FSI-1 and the FSI-2 to the gas turbine engine;
coupling a first control system to the FSI-1 and to the FSI-2, wherein the first control system includes a first driver A and a second driver A;
coupling a second control system to the FSI-1 and to the FSI-2, wherein the second control system includes a first driver B and a second driver B;
configuring the first control system to apply a first over-speed logic algorithm to determine operation of at least one of the first driver A, the second driver A, the first driver B, and the second driver B, and to apply a second over-speed logic algorithm to determine operation of at least one of the first driver A, the second driver A, the first driver B, and the second driver B; and
configuring the second control system to apply the first over-speed logic algorithm to determine operation of at least one of the first driver A, the second driver A, the first driver B, and the second driver B, and to apply the second over-speed logic algorithm to determine operation of at least one of the first driver A, the second driver A, the first driver B, and the second driver B.
2. A method in accordance with claim 1, wherein configuring the first control system comprises configuring the first control system to apply the first over-speed logic algorithm to determine operation of the first driver A and to apply the second over-speed logic algorithm to determine operation of the second driver A.
3. A method in accordance with claim 1, wherein configuring the second control system comprises configuring the second control system to apply the first over-speed logic algorithm to determine operation of the first driver B and to apply the second over-speed logic algorithm to determine operation of the second driver B.
4. A method in accordance with claim 1, wherein coupling one of the FSI-1 and the FSI-2 to the gas turbine engine comprises coupling one of the FSI-1 and the FSI-2 to a fuel throttlingshutoff valve configured to discontinue fuel flow to a combustor of the gas turbine engine upon receipt of an over-speed signal from the FSI-1 and the FSI-2.
5. A method in accordance with claim 1, further comprising configuring a first set of logic sensors to collect operating information from the engine, and a second set of logic sensors that are independent from the first set of logic sensors, to collect operating information from the engine.
6. A method in accordance with claim 5, further comprising configuring the first control system to receive engine operating information from at least one of the first set of logic sensors and the second set of logic sensors, and configuring the second control system to receive engine operating information from at least one of the first set of logic sensors and the second set of logic sensors.
7. A method in accordance with claim 1, further comprising configuring the first over-speed logic algorithm to apply at least one of a first over-speed threshold and a first set of over-speed calculations, to determine operation of at least one of the first driver A, the second driver A, the first driver B, and the second driver B.
8. A method in accordance with claim 1, further comprising configuring the second over-speed logic algorithm to apply at least one of a second over-speed threshold and a second set of over-speed calculations, to determine operation of at least one of the first driver A, the second driver A, the first driver B, and the second driver B.
9. An over-speed protection system for a gas turbine engine including a rotor, said over-speed protection system comprising:
a fuel throttlingshutoff valve coupled to a fuel supply coupled to said gas turbine engine;
a first fuel system interface (FSI-1) coupled to said fuel throttlingshutoff valve;
a second fuel system interface (FSI-2) coupled to said FSI-1;
a first control system coupled to said FSI-1 and to said FSI-2, said first control system comprising a first driver A and a second driver A, said first control system programmed with a first logic algorithm and a second logic algorithm; and
a second control system coupled to said FSI-1 and said FSI-2, said second control system comprising a first driver B and a second driver B, said second control system programmed with the first logic algorithm and the second logic algorithm.
10. A system in accordance with claim 9, wherein said fuel throttlingshutoff valve is configured to discontinue fuel flow to said gas turbine engine upon receipt of an over-speed signal from said FSI-1 and said FSI-2.
11. A system in accordance with claim 9, wherein said first control system is configured to determine operation of said first driver A using the first logic algorithm, and to determine operation of said second driver A using the second logic algorithm.
12. A system in accordance with claim 9, wherein said second control system is configured to determine operation of said first driver B using the first logic algorithm, and to determine operation of said second driver B using the second logic algorithm.
13. A system in accordance with claim 9, wherein said FSI-1 comprises a servovalve coupled to a shutoff shuttle valve.
14. A system in accordance with claim 13, wherein said servovalve comprises an electro-hydraulic servovalve (EHSV).
15. A system in accordance with claim 9, wherein said FSI-2 comprises a servovalve coupled to a shutoff shuttle valve.
16. A system in accordance with claim 15, wherein said servovalve comprises an electro-hydraulic servovalve (EHSV).
17. A gas turbine engine comprising:
a rotor;
a fuel delivery system configured to supply fuel to said engine for operating said rotor; and
an over-speed protection system coupled to said fuel delivery system, said over-speed protection system comprising:
a fuel throttlingshutoff valve coupled to said fuel delivery system;
a first fuel system interface (FSI-1) coupled to said fuel throttlingshutoff valve;
a second fuel system interface (FSI-2) coupled to said FSI-1;
a first control system coupled to said FSI-1 and to said FSI-2, said first control system comprising a first driver A and a second driver A, said first control system programmed with a first logic algorithm and a second logic algorithm; and
a second control system coupled to said FSI-1 and said FSI-2, said second control system comprising a first driver B and a second driver B, said second control system programmed with the first logic algorithm and the second logic algorithm.
18. A system in accordance with claim 17, wherein said fuel throttlingshutoff valve is configured to discontinue fuel flow to said gas turbine engine upon receipt of an over-speed signal from said FSI-1 and said FSI-2.
19. A system in accordance with claim 17, said first control system configured to determine operation of said first driver A using the first logic algorithm, and to determine operation of said second driver A using the second logic algorithm.
20. A system in accordance with claim 17, said second control system configured to determine operation of said first driver B using the first logic algorithm, and to determine operation of said second driver B using the second logic algorithm.
The claims below are in addition to those above.
All refrences to claim(s) which appear below refer to the numbering after this setence.
1. A composite substrate comprising a seed crystal substrate and a layer of a crystal of a nitride of a group 13 element grown on said seed crystal substrate, said seed crystal substrate comprising a base body and a plurality of rows of stripe-shaped seed crystal layers formed on said base body:
wherein an upper face of said seed crystal layer is (11-22) plane;
wherein a groove is formed between said seed crystal layers adjacent to each other, and;
wherein a longitudinal direction of said groove is a direction in which a c-axis of a crystal forming said seed crystal layer is projected on said upper face.
2. The composite substrate of claim 1, wherein said seed crystal layer has a side face facing said groove and of m-plane.
3. The composite substrate of claim 1, wherein a plurality of said seed crystal layers are separated from each other.
4. The composite substrate of claim 1, wherein said seed crystal layer comprises gallium nitride single crystal.
5. The composite substrate of claim 1, wherein said layer of said crystal of said nitride of said group 13 element comprises gallium nitride crystal.
6. The composite substrate of claim 1, wherein said layer of said crystal of said nitride of said group 13 element is polished.
7. A functional device comprising said composite substrate of claim 1, and a functional layer comprising a nitride of a group 13 element and formed on said layer of said crystal of said nitride of said group 13 element by vapor phase method.
8. The functional device of claim 7, wherein said functional layer has a function of emitting light.
9. A seed crystal substrate comprising a base body and a plurality of rows of stripe-shaped seed crystal layers formed on said base body:
wherein an upper face of said seed crystal layer is (11-22) plane;
wherein a groove is formed between said seed crystal layers adjacent to each other, and;
wherein a longitudinal direction of said groove is a direction in which a c-axis of a crystal forming said seed crystal layer is projected on said upper face.
10. The seed crystal substrate of claim 9, wherein said seed crystal layer has a side face facing said groove and of m-plane.
11. The seed crystal substrate of claim 9, wherein a plurality of said seed crystal layers are separated from each other.
12. The seed crystal substrate of claim 9, wherein said seed crystal layer comprises gallium nitride single crystal.