EP1063402A2
Expired / Lapsed
EP
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Method of operation of industrial gas turbine for optimal performance
Assignee: General Electric Co
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Filing: 2000-06-08
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Granted: —
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Expires: 2020-06-08
Abstract
Abstract A gas turbine operational strategy is provided for the optimization of ISO-Day rated performance. The invention is realized by setting the nominal operating line equal to or slightly below the operating limit line, so that ISO full load performance is maximized. Thus, the first stage turbine nozzle throat area is sized such that, without inlet bleed heat addition, and at Base-Load pressure ratio and firing temperature, the compressor operates within its operational limits on a ISO day. As ambient conditions change, levels of inlet bleed heat and firing temperature are controlled and the inlet guide vane angle is set whereby the nominal operating line is equal to or slightly below the operating limit line.
Inventors
- 👤 Philip Lynn Andrew
- 👤 Daniel Robert Dwyer
- 👤 Paul Thomas Marks
- 👤 John David Stampfli
- 👤 Joseph Anthony Cotroneo
- 👤 Ronald Richard Wesorick
- 👤 Harold Edward Miller
Bibliographic Details
Application Number
—
Jurisdiction
EP
Data Source
google_patents
Last Synchronized
2026-11-01 22:58
CPC Classifications
F; F02; F02C; F02C9/00; F02C9/26; F02C9/28; F02C7/00; F02C7/04; F02C7/057; F04; F04D; F04D27/00; F04D27/02; F05; F05D; F05D2270/00; F05D2270/01; F05D2270/05; Y; Y02; Y02E; Y02E20/00; Y02E20/16
Claims Analysis
Total Claims: 10
Claim 1
Independent Claim
220 words
A method of controlling a gas turbine to optimize
performance thereof, comprising: providing a control system including a controller
coupled to a plurality of turbine actuator systems, said
actuator systems being coupled to a gas turbine that
includes a compressor, a combustor, and a combustion
turbine, so as to control the operation of the gas turbine
in response to respective actuator system control signals
generated by the controller, said control system further
comprising an operator interface; the controller comprising
a processor for generating said respective actuator system
control signals in correspondence with input from said
operator interface and a plurality of turbine operating
condition signals, said control system being programmed to
define a pressure ratio operating limit line that provides
a substantially constant surge margin from a surge line
defined by pressure ratios associated with physical limits
to compressor operation for the gas turbine; sizing a first-stage turbine nozzle throat area of
said gas turbine so as to maximize an ISO pressure ratio
thereof, and operating said control system so that a nominal
operating line of the gas turbine is equal to or slightly
below said operating limit line, whereby a substantially
constant margin is maintained between the operational
pressure ratio of the gas turbine and pressure ratios
associated with operational limits at elevated pressure
ratios near the surge line.
Claim 2
Dependent Claim
39 words
A method as in claim 1, wherein said control system
is operated to maintain said substantially constant margin
by at least one of elevating inlet bleed heat, depressing
firing temperature, and limiting minimum operation inlet
guide vane angle setting.
Claim 3
Dependent Claim
39 words
A method as in claim 1 or 2, wherein said step of
operating comprises selectively applying elevated levels of
inlet bleed heat during Power Turn-Down operation to lower
the compressor operating line, thereby to maintain said
substantially constant margin.
Claim 4
Dependent Claim
57 words
A method as in claim 1, 2 or 3, wherein said step
of operating comprises selectively applying elevated levels
of inlet bleed heat during ColdDay operation in order to
minimize excursion to higher corrected speed, and thereby
minimize a need to lower the compressor operating line by
decreasing firing temperature, thereby to maintain said
substantially constant margin.
Claim 5
Independent Claim
56 words
A method as in any preceding claim, wherein said
step of operating comprises selectively applying elevated
levels of inlet bleed heat during Power Turn-Down operation
in order to minimize excursion to higher corrected speed,
and thereby minimize a need to lower the compressor
operating line by decreasing firing temperature, thereby to
maintain said substantially constant margin.
Claim 6
Dependent Claim
31 words
A method as in claim 1 or 2, wherein said step of
operating said control system comprises selectively
depressing firing temperature during Cold-Day operation,
thereby to maintain said substantially constant margin.
Claim 7
Dependent Claim
33 words
A method as in claim 1, 2 or 6, wherein said step
of operating said control system comprises selectively
depressing firing temperature during Power Turn-Down
operation, thereby to maintain said substantially constant
margin.
Claim 8
Dependent Claim
39 words
A method as in claim 1 or 2, said step of operating
said control system comprises selectively limiting Power
Turn-Down flow reduction by limiting the minimum operation
inlet guide vane angle setting, thereby to maintain said
substantially constant margin.
Claim 9
Independent Claim
45 words
A method as in any preceding claim, said step of
sizing comprises sizing said first-stage turbine nozzle
throat area such that, without inlet bleed heat addition,
and at Base-Load pressure ratio and firing temperature, the
compressor operates within its operational limits on an ISO
Day.
Claim 10
Independent Claim
24 words
A method as in any preceding claim, wherein said
operational limits include the onset of rotating stall, and
the onset of excessive blade strains.
References Cited (Backward Citations)
No citation records indexed.
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