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Fuel system for gas turbine starter

A fuel system and gas turbine technology, applied in turbine/propulsion fuel delivery system, gas turbine device, fuel valve of turbine/propulsion device, etc., can solve the problems of delayed ignition time, large smoke exhaust, open flame, etc., and achieve short ignition time , The effect of high fuel atomization quality and high ignition efficiency

Active Publication Date: 2020-05-22
上海尚实航空发动机股份有限公司
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The purpose of the present invention is to provide a fuel system for a gas turbine starter to solve the problems in the prior art that due to fuel flow fluctuations will cause deflagration at start, delayed ignition time, large smoke exhaust at shutdown, and even open flames technical problem

Method used

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  • Fuel system for gas turbine starter
  • Fuel system for gas turbine starter
  • Fuel system for gas turbine starter

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Embodiment Construction

[0026] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some, not all, embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention.

[0027] Such as figure 1 , figure 2 As shown, the present invention provides a fuel system for a gas turbine starter, comprising: a fuel ring 1, a fuel pump, and several atomizing nozzles 2 arranged on the fuel ring 1; the fuel ring 1 is installed on the gas On the casing 6 of the combustion chamber of the turbine starter; the fuel ring 1 is connected into a ring by means of multiple oil pipes 11 and multiple atomizing nozzles 2 alternately welded at intervals. Of...

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Abstract

The invention discloses a fuel system for a gas turbine starter. The fuel system comprises a fuel ring, a fuel pump and a plurality of atomizing nozzles arranged on the fuel ring, wherein the fuel ring is mounted in a combustion chamber of the gas turbine starter; the fuel pump is located outside the gas turbine starter and is connected to the fuel ring through a fuel pipe; part of the atomizing nozzles comprise built-in one-way valves, the one-way valves are arranged in the front of the atomizing nozzles, and the atomizing nozzles with the built-in one-way valves are arranged in central symmetry. By arranging the built-in one-way valves in part of the atomizing nozzles, the fuel pressure in the fuel ring reaches the pressure needed by atomization of the atomizing nozzles quickly, and fuelis atomized and sprayed quickly from the atomizing nozzles without the built-in one-way valves, so that the fuel atomizing quality during ignition can be improved, the ignition time is shortened andthe ignition efficiency is improved. The fuel system has the advantages of simple structure and good operating stability.

Description

technical field [0001] The invention relates to the field of aeroengines, in particular to a fuel system for a gas turbine starter. Background technique [0002] The fuel system is a key component of the gas turbine starter. It is necessary to ensure the fuel flow required by the starter in each state process, which determines the overall performance of the starter. The fuel system is generally composed of fuel pump, fuel filter, fuel ring, nozzle and other parts. The fuel pump starts first, and the fuel is atomized through the oil filter, stop valve, oil pipe, fuel injection ring, and nozzle, and then enters the starter combustion chamber for combustion. When the fuel pump is turned off, the fuel supply will be stopped and the starter will stop. Due to the fluctuation of fuel flow during the start and stop of the gas turbine starter, it will cause deflagration at start, delayed ignition time, large smoke exhaust at stop, and even open flames, etc., which will affect the s...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02C7/22F02C7/232F02C7/277
CPCF02C7/22F02C7/232F02C7/277
Inventor 黄啸王石柱
Owner 上海尚实航空发动机股份有限公司
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