Systems and methods involving multiple torque paths for gas turbine engines
US-2018187605-A1 · Jul 5, 2018 · US
Gas turbine engine shaft break mitigation
US11428117B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-11428117-B2 |
| Application number | US-202016749109-A |
| Country | US |
| Kind code | B2 |
| Filing date | Jan 22, 2020 |
| Priority date | Feb 4, 2019 |
| Publication date | Aug 30, 2022 |
| Grant date | Aug 30, 2022 |
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Abstract
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A method is provided of controlling a gas turbine having a shaft connecting a compressor to a turbine, as well as having a reheat system, and a gas turbine. The method includes the steps of: operating the engine using the reheat system to provide a mass flow rate of reheat fuel into a gas flow of the gas turbine engine downstream of an exit of the turbine; detecting a shaft break event in the shaft; and in response to this detection, maintaining the mass flow rate of the reheat fuel being provided into the gas flow downstream of the turbine exit, whereby the maintained mass flow rate of reheat fuel raises a back pressure downstream of the turbine and thereby reduces a rotational speed of the turbine.
First claim
Opening claim text (preview).
What is claimed is: 1. A method of controlling a gas turbine engine having a shaft connecting a compressor to a turbine and further having a reheat system, the method including the steps of: operating the gas turbine engine using the reheat system to provide a mass flow rate of reheat fuel into a gas flow of the gas turbine engine downstream of an exit of the turbine; detecting a shaft break event in the shaft; and in response to the detecting, maintaining and/or increasing the mass flow rate of the reheat fuel being provided into the gas flow downstream of the turbine exit, whereby the maintaining and/or increasing of the mass flow rate of reheat fuel creates a back pressure downstream of the turbine sufficient to reduce a rotational speed of the turbine. 2. The method of claim 1 , wherein the step of maintaining and/or increasing the mass flow rate of the reheat fuel being provided into the gas flow downstream of the turbine exit is performed by maintaining a fuel schedule for the reheat system in a pre-shaft break event configuration. 3. The method of claim 1 , whereby the back pressure downstream of the turbine moves a working line of the compressor towards a surge region. 4. A non-transitory computer readable medium storing a computer program comprising code which, when run on a computer, causes the computer to perform the method of claim 1 . 5. A computer system programmed to perform the method of claim 1 . 6. A gas turbine engine, comprising: a shaft connecting a compressor to a turbine; a reheat system; and an electronic engine controller; wherein the electronic engine controller is configured to: operate the gas turbine engine using the reheat system to provide a mass flow rate of reheat fuel into a gas flow of the gas turbine engine downstream of an exit of the turbine; detect a shaft break event in the shaft; and in response to detection of the shaft break event, maintain and/or increase the mass flow rate of the reheat fuel being provided into the gas flow downstream of the turbine exit thereby creating a back pressure downstream of the turbine sufficient to reduce a rotational speed of the turbine. 7. The gas turbine engine of claim 6 , wherein the electronic engine controller is configured to maintain and/or increase the mass flow rate of the reheat fuel being provided into the gas flow downstream of the exit of the turbine by maintaining a fuel schedule for the reheat system in a pre-shaft break event configuration. 8. The gas turbine engine of claim 6 , wherein creating the back pressure downstream of the turbine moves a working line of the compressor towards a surge region. 9. An aircraft, including the gas turbine engine of claim 6 .
Assignees
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Classifications
Spool rotational speed · CPC title
Thrust · CPC title
Control of fuel supply conjointly with another control of the plant (with nozzle section control F02K1/17) · CPC title
Restoring position · CPC title
to prevent overspeed · CPC title
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- What does patent US11428117B2 cover?
- A method is provided of controlling a gas turbine having a shaft connecting a compressor to a turbine, as well as having a reheat system, and a gas turbine. The method includes the steps of: operating the engine using the reheat system to provide a mass flow rate of reheat fuel into a gas flow of the gas turbine engine downstream of an exit of the turbine; detecting a shaft break event in the s…
- Who is the assignee on this patent?
- Rolls Royce Plc
- What technology area does this patent fall under?
- Primary CPC classification F01D21/02. Mapped technology areas include Mechanical Engineering.
- When was this patent published?
- Publication date Tue Aug 30 2022 00:00:00 GMT+0000 (Coordinated Universal Time) (B2). Legal status and post-grant events are not shown on this page.
- What related patents are in patentsdb?
- We list 3 related publications on this page (citations in our corpus or others sharing the same primary CPC).