System and method for controlling dual starter air valve

Patent metadata

Field	Value
Publication number	US-11401868-B2
Application number	US-202017021714-A
Country	US
Kind code	B2
Filing date	Sep 15, 2020
Priority date	Nov 7, 2016
Publication date	Aug 2, 2022
Grant date	Aug 2, 2022

Abstract

A system may comprise a sensor configured to measure a characteristic of an engine component. A valve assembly may have an airflow outlet in fluid communication with the engine component. The valve assembly may include a first valve. A first valve control device may be coupled to the first valve and configured to control the first valve based on a measurement by the sensor. A second valve may be in fluidic series with the first valve. A second valve control device may be coupled to the second valve and configured to control the second valve based on the measurement by the sensor.

First claim

What is claimed is:

1. A method of controlling a rotational speed of a gas turbine engine during start-up, comprising: receiving, by a valve assembly, an input airflow having an input pressure, the valve assembly including a first valve and a second valve, the second valve in fluidic series with the first valve;
measuring the rotational speed of the gas turbine engine;
determining, by a full authority digital engine control (FADEC), an engine speed adjustment based on the rotational speed, a second position of at least one of the first valve or the second valve, and a desired speed;
controlling, by the FADEC, an output pressure of an output airflow by controlling a position at least one of the first valve and the second valve based on the engine speed adjustment and the desired speed, and in response, controlling the output pressure at an airflow outlet of the valve assembly to maintain the rotational speed at the desired speed;
determining, by the FADEC, a valve condition, the valve condition corresponding to a failure of the first valve;
pulse width modulating, by the FADEC, a solenoid of the second valve in response to the valve condition to regulate an airflow through the valve assembly; and
delivering the output airflow to an air turbine starter coupled to the gas turbine engine.

2. The method of claim 1 , wherein the first valve comprises a torque motor servovalve and wherein the positioning the at least one of the first valve and the second valve further comprises delivering a current to the torque motor servovalve to adjust the position of the first valve.

3. The method of claim 2 , wherein the positioning the at least one of the first valve and the second valve further comprises locking the second valve in an open position while adjusting the position of the first valve.

4. The method of claim 1 wherein the positioning the at least one of the first valve and the second valve further comprises pulse width modulating the solenoid between an on state and an off state.

5. The method of claim 4 , wherein the positioning the at least one of the first valve and the second valve further comprises locking the first valve in an open position while pulse width modulating the solenoid.

6. The method of claim 1 , further comprising decreasing the output pressure of the output airflow to reduce the rotational speed of the gas turbine engine.

7. A system for a gas turbine engine, comprising: an air turbine starter operatively coupled to the gas turbine engine and configured to rotate the gas turbine engine during a startup condition;
a valve assembly having an airflow outlet in fluid communication with the air turbine starter, the valve assembly including:
a first valve, a first valve control device coupled to the first valve and configured to control the first valve, and wherein the first valve control device is configured to control a pressure at the airflow outlet of the valve assembly;
a second valve in fluidic series with the first valve,
a second valve control device coupled to the second valve and configured to control the second valve, the second valve control device comprising a solenoid;

a full authority digital engine control (FADEC) coupled to the valve assembly;
a sensor configured to measure a rotational speed of the gas turbine engine; and
a tangible, non-transitory memory configured to communicate with the FADEC, the tangible, non-transitory memory having instructions stored thereon that, in response to execution by the FADEC, cause the FADEC to perform operations comprising:
receiving, by the FADEC, a rotational speed measurement from the sensor;
determining, by the FADEC, an engine speed adjustment based on the rotational speed measurement, a second position of at least one of the first valve or the second valve, and a desired speed;
generating, by the FADEC, a command for at least one of the first valve control device or the second valve control device based on the engine speed adjustment and the desired speed;
sending, by the FADEC, the command to at least one of the first valve control device or the second valve control device and, in response, controlling the pressure at the airflow outlet of the valve assembly to maintain the rotational speed measurement at the desired speed;
determining, by the FADEC, a valve condition, the valve condition corresponding to a failure of the first valve; and
pulse width modulating, by the FADEC, the solenoid of the second valve control device in response to the valve condition to regulate an airflow through the valve assembly.

8. The system of claim 7 , wherein the first valve control device comprises a torque motor servovalve.

9. The system of claim 8 , wherein the torque motor servovalve is configured to receive the command from the FADEC and to position the first valve.

10. The system of claim 9 , wherein the solenoid is configured to receive the command from the FADEC and to open or close the second valve.

11. The system of claim 7 , wherein the second valve comprises a second piston, and wherein a third position of the second piston is configured to control the pressure at the airflow outlet of the valve assembly.

12. The system of claim 7 , wherein the first valve control device and the second valve control device are in electrical communication with the FADEC, and wherein the first valve control device comprises a first torque motor servovalve and the second valve control device comprises a second torque motor servovalve.

13. The system of claim 7 , further comprising a means of positioning the first valve control device.

14. The system of claim 7 , further comprising a means of opening or closing the first valve control device.

Assignees

• Raytheon Tech Corp

Inventors

• Greenberg Michael D
• Goodman Robert
• Dehais John M

Classifications

• F02C9/16

  Control of working fluid flow (F02C9/48 takes precedence; control of air-intake flow F02C7/057) · CPC title

• F01D17/205

  Centrifugal governers directly linked to valves · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F05D2270/304

  Spool rotational speed · CPC title

• F02C7/277 Primary

  the starter being a {separate} turbine · CPC title