Fuel supply to the combustion chamber of gas turbine engine (optional), a gas turbine engine, the control method of gas turbine engines and gas turbine engines MODERNIZATION PROCESS

摘要

1. fuel supply device in the camera u0441u0433u043eu0440u0430u043du0438u00a0 gas turbine u0434u0432u0438u0433u0430u0442u0435u043bu00a0 containing u0446u0435u043du0442u0440u043eu0431u0435u0436u043du0443u044e the nozzle and nozzle u043eu0442u043bu0438u0447u0430u044eu0449u0435u0435u0441u00a0, u0446u0435u043du0442u0440u043eu0431u0435u0436u043du0430u00a0 u0438u043cu0435u0435 fuel injector t the central axis, and the nozzle is located asymmetrically about the axis and has u0443u043fu043eu043cu00a0u043du0443u0442u043eu0439 output end with a group of vent holes.;2. device for u043eu0442u043bu0438u0447u0430u044eu0449u0435u0435u0441u00a0 1, so that it further contains a bar passing through a central axis, and is asymmetrical, with the possibility of u0441u043eu0437u0434u0430u043du0438u00a0 the reduced flow of fuel from the side opposite to the u0443u043fu043eu043cu00a0u043du0443u0442u043eu0439, compared with the flow of the u0443u043fu043eu043cu00a0u043du0443u0442u043eu0439 bar.;3. device for u043eu0442u043bu0438u0447u0430u044eu0449u0435u0435u0441u00a0 1, so that the u0430u0441u0441u0438u043cu0435u0442u0440u0438u0447u043du043eu0441u0442u044c further u043eu0431u0440u0430u0437u0443u0435u0442u0441u00a0 fulfilling the first of u0443u043fu043eu043cu00a0u043du0443u0442u044bu0445 vent holes with smaller size than that of the steel u0443u043fu043eu043cu00a0u043du0443u0442u044bu0435 graduations u043eu0442u0432u0435u0440u0441u0442u0438u00a0.;4. device for u043eu0442u043bu0438u0447u0430u044eu0449u0435u0435u0441u00a0 1, so that the u0430u0441u0441u0438u043cu0435u0442u0440u0438u0447u043du043eu0441u0442u044c further u043eu0431u0440u0430u0437u0443u0435u0442u0441u00a0 uneven of vent holes on the circumference around the u0443u043fu043eu043cu00a0u043du0443u0442 oh, the central axis.;5. device for u043eu0442u043bu0438u0447u0430u044eu0449u0435u0435u0441u00a0 p.4, however, that the location is accomplished by one interval on the circumference between the outlets u043eu0442u0432u0435u0440u0441u0442u0438u00a0u043cu0438, size b u043eu043bu044cu0448u0435u0433u043e than other intervals on the circumference between the outlets u043eu0442u0432u0435u0440u0441u0442u0438u00a0u043cu0438.;6. device for u043eu0442u043bu0438u0447u0430u044eu0449u0435u0435u0441u00a0 1, so that the u0443u043fu043eu043cu00a0u043du0443u0442u044bu0435 u043eu0442u0432u0435u0440u0441u0442u0438u00a0 graduations are located on the same u0440u0430u0434u0438u0430u043bu044cu043du043eu043c u0440u0430u0441u0441u0442u043eu00a0u043du0438u0438 from u0443u043fu043eu043cu00a0u043du0443u0442u043eu0439 central axis, and the number of as of 4 to 12.;7.turboshaft, u043eu0442u043bu0438u0447u0430u044eu0449u0438u0439u0441u00a0 because it contains u043au043eu043cu043fu0440u0435u0441u0441u043eu0440u043du0443u044e section ring cell u0441u0433u043eu0440u0430u043du0438u00a0 installed with the possibility of u043fu043eu0441u0442u0443u043fu043bu0435u043du0438u00a0 in her u0432u043eu0437u0434u0443 ha from the compressor section, and u0442u0443u0440u0431u0438u043du043du0443u044e section, installed with the possibility of u043fu043eu0441u0442u0443u043fu043bu0435u043du0438u00a0 gaseous products from the chamber u0433u043eu0440u0435u043du0438u00a0 u0441u0433u043eu0440u0430u043du0438u00a0 and u043fu0440u0438u0432u0435u0434u0435u043du0438u00a0 in u0434u0435u0439u0441u0442u0432 s the compressor section.the chamber contains a group of devices located on the circumference of the u0441u0433u043eu0440u0430u043du0438u00a0 fuel in turboshaft, each of which contains u0446u0435u043du0442u0440u043eu0431u0435u0436u043du0443 yu the nozzle with the central axis and the nozzle located asymmetrically about the axis and having a u0443u043fu043eu043cu00a0u043du0443u0442u043eu0439 output end with a group of vent holes.;8. engine on p.7, u043eu0442u043bu0438u0447u0430u044eu0449u0438u0439u0441u00a0 as foreseen from 12 to 30 u0443u043fu043eu043cu00a0u043du0443u0442u044bu0445 devices for fuel.;9. engine on p.7, u043eu0442u043bu0438u0447u0430u044eu0449u0438u0439u0441u00a0, u0430u0441u0441u0438u043cu0435u0442u0440u0438u0447u043du043eu0441u0442u044c further u043eu0431u0440u0430u0437u0443u0435u0442u0441u00a0) the first part of the nozzle further inside of the second part of the reduction pot from the first part of the nozzle of the fuel than u0434u043eu043fu043eu043bu043du00a0u044eu0449u0435u0439 its second part.;10.a gas turbine engine u0443u043fu0440u0430u0432u043bu0435u043du0438u00a0 containing u043au043eu043cu043fu0440u0435u0441u0441u043eu0440u043du0443u044e section ring cell u0441u0433u043eu0440u0430u043du0438u00a0 installed with an air of u043fu043eu0441u0442u0443u043fu043bu0435u043du0438u00a0 com u043fu0440u0435u0441u0441u043eu0440u043du043eu0439 section and a panel located on the circumference of the fuel supply device, and u0442u0443u0440u0431u0438u043du043du0443u044e sectionthe possibility of u043fu043eu0441u0442u0443u043fu043bu0435u043du0438u00a0 gaseous products from the chamber u0433u043eu0440u0435u043du0438u00a0 u0441u0433u043eu0440u0430u043du0438u00a0 and u043fu0440u0438u0432u0435u0434u0435u043du0438u00a0 in the compressor section, in which an warm all of the devices u043eu0441u0443u0449u0435u0441u0442u0432u043bu00a0u044eu0442 with the greater amount of fuel from the outer parts of the u0434u043eu043fu043eu043bu043du00a0u044eu0449u0438u0445 devices than their internal parts of the device.;11. method for u043eu0442u043bu0438u0447u0430u044eu0449u0438u0439u0441u00a0 p.10, so that the fuel flow through the external part of the device u0441u043eu0441u0442u0430u0432u043bu00a0u0435u0442 at least 110% of fuel consumption in the internal part of the device.;12.a gas turbine u0434u0432u0438u0433u0430u0442u0435u043bu00a0 modernization, which are the basic design u0443u043fu043eu043cu00a0u043du0443u0442u043eu0433u043e u0434u0432u0438u0433u0430u0442u0435u043bu00a0 containing ring cell u0441u0433u043eu0440u0430u043du0438u00a0 with u043au0440u0443u0433u043e the basic devices u0432u043eu0435 centrifugal nozzle / nozzle, each of which contains u0446u0435u043du0442u0440u043eu0431u0435u0436u043du0443u044e the nozzle with a central axis, and a nozzlean output end with a group of vent holes around the u0443u043fu043eu043cu00a0u043du0443u0442u043eu0439 axis and located symmetrically about the u0443u043fu043eu043cu00a0u043du0443u0442u043eu0439 axiswhich u0438u0437u043cu0435u043du00a0u044eu0442 centrifugal nozzle or nozzles on the u0430u0441u0441u0438u043cu0435u0442u0440u0438u0447u043du043eu0435 through one of the parameters u0438u0437u043cu0435u043du0435u043du0438u00a0 u0430u0441u0441u0438u043cu043cu0435u0442u0440u0438u0438 and form the u0440u0430u0441u043fu0440u0435u0434u0435u043bu0435 the temperature in the chamber u0441u0433u043eu0440u0430u043du0438u00a0 in accordance with an arrangement of the centrifugal nozzle or nozzles.;13. way on p.12, which receive the distribution of temperature of the centrifugal nozzle or nozzles are more equal than the distribution of the temperature in the core u0440u0430u0441u043fu043eu043bu043e of the centrifugal nozzle or nozzles.;14. method for u043eu0442u043bu0438u0447u0430u044eu0449u0438u0439u0441u00a0 p.12, so that u043fu0440u0438u043cu0435u043du00a0u044eu0442 at least partially computer simulations.;15. fuel supply device in turboshaft, which u0446u0435u043du0442u0440u043eu0431u0435u0436u043du0443u044e the nozzle and nozzle u043eu0442u043bu0438u0447u0430u044eu0449u0435u0435u0441u00a0, u0446u0435u043du0442u0440u043eu0431u0435u0436u043du0430u00a0 fuel injector has a central axis a nozzle is off the end with a group of vent holes, u00a0u0432u043bu00a0u044eu0449u0438u0445u0441u00a0 means u043eu0433u0440u0430u043du0438u0447u0435u043du0438u00a0 u0433u043eu0440u00a0u0447u0438u0445 u043fu00a0u0442u0435u043d of u0433u043eu0440u0435u043du0438u00a0.