FIELD: aviation gas turbine engine building.
SUBSTANCE: group of inventions is intended for automatic protection of a gas turbine engine (GTE) from uncontrolled spin-up of a power turbine rotor. A method for protecting a gas turbine engine from spinning up a power turbine rotor is presented, in which the disconnection of the power turbine rotor from the load rotor is established, control signals are issued to stop the supply of fuel to the combustion chamber simultaneously to the pump-regulator and the shut-off device located between the pump-regulator and at least one fuel manifold. So, with the help of a cut-off device, the fuel manifold inlet is additionally connected to a cavity having a medium pressure less than the pressure in the combustion chamber, the fuel pressure at the fuel manifold inlet is reduced to the pressure level in the specified cavity, a reverse fuel pressure drop is created on all injectors and the fuel manifold, the outflow of fuel into the combustion chamber from all injectors simultaneously is stopped and then fuel is removed from all injectors and the fuel manifold into the specified cavity; communication of the inlet to at least one fuel manifold with a cavity having a pressure of the medium less than the pressure in the combustion chamber is carried out by a cut-off device through the outlet channel, depressurizing the inlet to the aforementioned outlet channel. In addition, a device for protecting the gas turbine engine from spinning up the power turbine rotor is also presented.
EFFECT: reduced time for stopping the supply of fuel to the combustion chamber when the disconnection of the power turbine rotors and the load is detected, as a result of which the margin between the maximum achievable speed of the power turbine rotor after disconnection from the load rotor and the speed at which the power turbine is destroyed is increased.
11 cl, 3 dwg
Title | Year | Author | Number |
---|---|---|---|
MULTI-COLLECTOR DEVICE FOR FUEL SUPPLY TO THE CAMERA OF COMBUSTION OF A GAS TURBINE ENGINE | 2017 |
|
RU2664900C1 |
METHOD AND SYSTEM FOR SUPPLYING FUEL TO COMBUSTION CHAMBER OF GAS-TURBINE ENGINE | 1992 |
|
RU2034166C1 |
METHOD FOR STARTING GAS TURBINE ENGINE ON CRYOGENIC FUEL | 2021 |
|
RU2772515C1 |
TURBOPROP GAS TURBINE ENGINE | 2007 |
|
RU2359131C1 |
METHOD FOR PROTECTION OF DUAL-FROW TURBOJET ENGINE AGAINST LOW PRESSURE TURBINE SPIN-UP | 2015 |
|
RU2602644C1 |
GAS TURBINE LOCOMOTIVE AND ITS POWER PLANT | 2008 |
|
RU2370386C1 |
METHOD OF GAS TURBINE ENGINE PROTECTION | 2008 |
|
RU2376487C2 |
RETURN STAGE OF ROCKET VEHICLE, METHOD OF ITS OPERATION AND GAS TURBINE ENGINE | 2015 |
|
RU2609664C1 |
TURBOPROP GAS TURBINE ENGINE | 2007 |
|
RU2359132C1 |
GAS TURBINE UNIT | 2008 |
|
RU2379533C1 |
Authors
Dates
2023-07-04—Published
2023-02-17—Filed