Patent US3759037A successfully refreshed from Google Patents.
US3759037A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Over temperature protection system for a gas turbine
Assignee: Westinghouse Electric Corp
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Filing: 1972-01-27
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Granted: 1973-09-18
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Expires: 1992-01-27
Abstract
Abstract A system to protect the turbine against transient high temperatures during the ignition period of a gas turbine. The protection system measures the pressure or flow rate of the fuel entering the turbine. If the pressure or flow rate exceeds a value which will produce an over temperature condition, a signal is sent to a fuel shutoff valve to interrupt the fuel flow to the turbine.
Inventors
- 👤 R Kiscaden
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-25 14:43
CPC Classifications
F; F02; F02C; F02C7/00; F02C7/26
Claims Analysis
Total Claims: 7
Claim 1
Independent Claim
128 words
In a gas turbine power plant having a rotor structure rotatable at a low speed during a cranking period and at an intermediate speed during an ignition period, a system for protecting the rotor structure from an over temperature transient condition, said system comprising in combination: means responsive to the quantity of fuel supplied to the turbine during the ignition period, means to interrupt the flow of fuel to the turbine, signal applying means, said means responsive to the fuel supplied providing a signal to said signal applying means when the quantity of fuel supplied corresponds to a quantity which will produce an over temperature condition in said turbine, said signal applying means being adapted to activate said means to interrupt the flow of fuel to said turbine.
Claim 2
Dependent Claim
128 words
In a gas turbine power plant having a rotor structure rotatable at a low speed during a cranking period and at an intermediate speed during an ignition period, a system for protecting the rotor structure from an over temperature transient condition, said system comprising in combination: means responsive to the quantity of fuel supplied to the turbine during the ignition period, means to interrupt the flow of fuel to the turbine, signal applying means, said means responsive to the fuel supplied providing a signal to said signal applying means when the quantity of fuel supplied corresponds to a quantity which will produce an over temperature condition in said turbine, said signal applying means being adapted to activate said means to interrupt the flow of fuel to said turbine.
Claim 3
Dependent Claim
52 words
The system recited in claim 1, wherein the means responsive to the fuel supplied and the means for interrupting the flow of fuel are disposed in a fuel conduit upstream of the turbine, and said signal applying means comprises a solenoid valve which activates the means for interrupting the flow of fuel.
Claim 4
Dependent Claim
152 words
In a gas turbine comprising at least one combustion chamber, a rotor structure, said rotor structure being rotatable at a low speed during a cranking period, at an intermediate speed during an ignition period, and at a high speed during an operating period, and a system for protecting the rotor structure from a high temperature transient condition, said system comprising: pressure sensing means responsive to the pressure of the fuel flowing to said combustion chamber during said ignition period, said pressure sensing means providing a signal representative of the rate of flow of fuel to said combustion chamber, means to interrupt the flow of fuel to said combustion chamber, means for applying said signal to said means to interrupt fuel flow when said signal reaches a value corresponding to a rate of flow which will produce an over temperature condition in said turbine, if said rate of flow were allowed to continue.
Claim 5
Dependent Claim
152 words
In a gas turbine comprising at least one combustion chamber, a rotor structure, said rotor structure being rotatable at a low speed during a cranking period, at an intermediate speed during an ignition period, and at a high speed during an operating period, and a system for protecting the rotor structure from a high temperature transient condition, said system comprising: pressure sensing means responsive to the pressure of the fuel flowing to said combustion chamber during said ignition period, said pressure sensing means providing a signal representative of the rate of flow of fuel to said combustion chamber, means to interrupt the flow of fuel to said combustion chamber, means for applying said signal to said means to interrupt fuel flow when said signal reaches a value corresponding to a rate of flow which will produce an over temperature condition in said turbine, if said rate of flow were allowed to continue.
Claim 6
Dependent Claim
155 words
In a gas turbine comprising at least one combustion chamber, a rotor structure, said rotor structure being rotatable at a low speed during a cranking period, at an intermediate speed during an ignition period, and at a high speed during an operating period, and a system for protecting the rotor structure from a high temperature transient condition, said system comprising: flow rate sensing means responsive to the rate of flow of fuel to said combustion chamber during said ignition period, said flow rate sensing means providing a signal representative of the rate of flow of fuel flowing to said combustion chamber, means to interrupt the flow of fuel to said combustion chamber, means for applying said signal to said means to interrupt fuel flow when said signal reaches a value corresponding to a rate of flow which will produce an over termperature condition in said turbine, if said rate of flow were allowed to continue.
Claim 7
Dependent Claim
155 words
In a gas turbine comprising at least one combustion chamber, a rotor structure, said rotor structure being rotatable at a low speed during a cranking period, at an intermediate speed during an ignition period, and at a high speed during an operating period, and a system for protecting the rotor structure from a high temperature transient condition, said system comprising: flow rate sensing means responsive to the rate of flow of fuel to said combustion chamber during said ignition period, said flow rate sensing means providing a signal representative of the rate of flow of fuel flowing to said combustion chamber, means to interrupt the flow of fuel to said combustion chamber, means for applying said signal to said means to interrupt fuel flow when said signal reaches a value corresponding to a rate of flow which will produce an over termperature condition in said turbine, if said rate of flow were allowed to continue.
References Cited (Backward Citations)
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1976-09-17 | 1977-03-19 | 1977-09-18 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1980-09-17 | 1981-03-19 | 1981-09-18 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1984-09-17 | 1985-03-19 | 1985-09-18 | $7700.00 | Window Closed / Lapsed |