EP3578762A1 - Procédé pour déterminer une température de sortie d'un étage de combustion amont dans un moteur à turbine à gaz comportant au moins deux étages de combustion disposés en série - Google Patents

Procédé pour déterminer une température de sortie d'un étage de combustion amont dans un moteur à turbine à gaz comportant au moins deux étages de combustion disposés en série Download PDF

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Publication number
EP3578762A1
EP3578762A1 EP18176673.4A EP18176673A EP3578762A1 EP 3578762 A1 EP3578762 A1 EP 3578762A1 EP 18176673 A EP18176673 A EP 18176673A EP 3578762 A1 EP3578762 A1 EP 3578762A1
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EP
European Patent Office
Prior art keywords
temperature
upstream
expansion turbine
obtaining
combustion
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP18176673.4A
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German (de)
English (en)
Inventor
Stefano Bernero
Martin Gassner
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General Electric Technology GmbH
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General Electric Technology GmbH
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Filing date
Publication date
Application filed by General Electric Technology GmbH filed Critical General Electric Technology GmbH
Priority to EP18176673.4A priority Critical patent/EP3578762A1/fr
Publication of EP3578762A1 publication Critical patent/EP3578762A1/fr
Withdrawn legal-status Critical Current

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/003—Arrangements for testing or measuring
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/02—Arrangement of sensing elements
    • F01D17/08—Arrangement of sensing elements responsive to condition of working-fluid, e.g. pressure
    • F01D17/085—Arrangement of sensing elements responsive to condition of working-fluid, e.g. pressure to temperature

Definitions

  • the present disclosure relates to a method as set forth in the claims.
  • a gas turbine engine in which two combustion chambers are provided in a fluidly serial arrangement, such that a second of said combustion chambers receives exhaust gases from the first one of said combustion chambers, with an intermediate expansion turbine being fluidly interposed between the two combustion chambers.
  • the inlet temperature of the intermediate expansion turbine is an important process parameter for the operation of the gas turbine engine. A direct measurement of these temperatures under field conditions is not viable in an industrial use environment. It is known from expansion turbines to measure a temperature at the outlet of the expansion turbine, and derive the inlet temperature to the expansion turbine based upon the outlet temperature and a pressure ratio or pressure drop over the expansion turbine, whereas the calculation of the inlet temperature further takes into account characteristics of the specific expansion turbine.
  • the temperature downstream the intermediate expansion turbine, or upstream the second combustor, respectively, is measured, and the inlet temperature of the intermediate expansion turbine is calculated based upon said outlet temperature and pressure ratio with further consideration of the thermodynamic behaviour of the specific expansion turbine.
  • the person having ordinary skill in the art is perfectly familiar with the calculation of the expansion turbine inlet temperature based upon the expansion turbine outlet temperature and the pressure ratio over the expansion turbine.
  • the temperature downstream or at the outlet of the intermediate expansion turbine is still at a level significantly above that at the outlet of a last or most downstream expansion turbine in which the expansion to the final pressure of the gas turbine process takes place.
  • the temperature downstream the intermediate expansion turbine reaches values sufficiently high to enable a spontaneous ignition of fuel introduced into the second combustion chamber.
  • thermocouples used for determination of the outlet temperature of the intermediate expansion turbine need to operate under a harsh environment.
  • the pressure is still significantly elevated, such that extreme care must be taken of tightness of the feedthrough of instrumentation. The temperature measurement instrumentation requires careful maintenance.
  • the present disclosure relates to a method of the type initially mentioned. It is an objective of the herein disclosed subject matter to provide a method which enables the determination of a temperature at the outlet of an upstream combustion stage in a gas turbine having at least two serially arranged combustion stages.
  • An upstream combustion stage shall be understood as a combustion stage upstream of a last, most downstream combustion stage.
  • a method shall be provided which allows the required temperature determination without the need to place temperature sensors inside fluids which have temperatures and/or pressures beyond a certain threshold value. In this respect it may prove advantageous to have temperature sensors positioned in the working fluid no more than upstream of the most upstream combustion stage and downstream of the most downstream turbine.
  • a method for determining an outlet temperature of an upstream combustion stage in a gas turbine engine the gas turbine engine having at least two serially arranged combustion stages.
  • the temperatures referred to are working fluid temperatures.
  • a compressor is provided in fluid communication with and upstream a first, most upstream, of said combustion stages.
  • a last, most downstream, expansion turbine is provided in fluid communication with and downstream a last, most downstream, of said combustion stages. There may or may not be other expansion turbines present in the gas turbine engine. It is understood that the last expansion turbine is the turbine in which the working fluid of the gas turbine engine is expanded to a terminal, final pressure of the thermodynamic process of the gas turbine engine.
  • Said pressure is at least essentially equal to the pressure upstream the compressor, or, for air breathing gas turbine engines, the ambient pressure.
  • the pressure after the last expansion turbine might be slightly higher than the pressure at the compressor inlet or the ambient pressure, due to potential pressure losses for instance in an exhaust duct, a heat recovery steam generator, silencers, a scrubber, and other devices restricting an exhaust duct.
  • the last expansion turbine may in certain embodiments be the one and only expansion turbine of the gas turbine engine, while in other embodiments intermediate expansion turbines may be present and fluidly interposed between combustion stages.
  • the method comprises obtaining at least one first parameter representative of the inlet temperature of the last, most downstream, expansion turbine and/or the outlet temperature of the last, most downstream, of said combustion stages, obtaining at least one second parameter representative of the outlet temperature of the compressor and/or the inlet temperature of the first, most upstream, of said combustion stages, and obtaining the fuel massflows to each combustion stage and/or a fuel massflow ratio between the combustion stages.
  • An outlet temperature of an upstream combustion stage different from the most downstream combustion stage is then obtained, in particular calculated or computed, based upon said first and second parameters and the fuel massflows to the combustion stages and/or the fuel massflow ratios.
  • Upstream and downstream refer to the flow direction of the working fluid through the gas turbine engine.
  • Obtaining" a parameter or value is to be understood in a broad sense, and may comprise, while not being limited to, measuring a value or parameter directly or deriving a value or parameter from other values or parameters. It is in this respect understood that obtaining any of the at least one parameter representative of the inlet temperature of the last expansion turbine and/or the outlet temperature of the last of said combustion stages and the at least one second parameter representative of the outlet temperature of the compressor and/or the inlet temperature of the first of said combustion stages may in instances comprise a direct measurement of said at least one parameter. For instance, a compressor outlet temperature may typically be obtained through a direct measurement.
  • a compressor outlet temperature may be represented by a combination of other values, such as for instance, for a compressor with a known thermodynamic characteristic, by a combination of conditions at the compressor inlet and/or ambient conditions in case of an air breathing engine and/or a compressor pressure ratio and/or a variable inlet guide vane position. It may be necessary to consider other parameters, such as for instance a mass flow of liquid agent injected into the compressor. The skilled person is perfectly familiar with obtaining a compressor outlet temperature for a given compressor from such a set of parameters. Likewise, the temperature at the inlet of the last expansion turbine may for a given expansion turbine typically be determined based upon measurements of the exhaust temperature downstream the last expansion turbine and a pressure ratio over the expansion turbine in further consideration of the expansion turbine thermodynamic characteristics. The skilled person is also perfectly familiar with these calculations. The above examples are in no way to be considered as exhaustive, and the skilled person will readily be aware of or come up with an abundance of ways how to represent these temperatures.
  • temperatures are explicitly used in a calculation of the outlet temperature of the upstream combustion stage, or a formula and/or computer program used for calculation or computation, but it may well be sufficient of the parameters representative of the temperatures to appear in a suitable combination.
  • a "parameter representative of' a temperature may be broadly understood as a parameter having an influence on or being correlated with the said temperature, such that the parameter alone or in combination with other parameters may be used to calculate and/or to represent said temperature. This parameter may thus be said to represent the temperature, and in particular changes of said parameter cause changes of the temperature.
  • the fuel massflow ratio is representative of the relative fuel massflows to the different combustion stages. It may be represented as the ratio of the partial fuel massflows to the different combustion stages to each other, but also as partial fuel mass flows related to the total fuel mass flow to all combustion stages, and other parameters the skilled person may deem appropriate.
  • the fuel massflow ratio may be obtained from measured mass flows, but may in certain embodiments be obtained from control signals and/or control valve positions and/or measured fuel pressures.
  • the pressures and temperatures at the inlet and outlet of certain components of a gas turbine engine referred to are working fluid temperatures and pressures. Further, the pressures and temperatures referred to in the context of this application generally mean total pressures and temperatures, that is, the pressure and temperature of the fluid when it has isentropically been decelerated to a standstill, including the dynamic pressure head of a fluid flow and the temperature which corresponds to the kinetic energy of a fluid flow.
  • an intermediate expansion turbine may be provided and fluidly interposed between two combustion stages. It is readily appreciated that in such instances the outlet temperature of a combustion stage immediately upstream an intermediate expansion turbine equals or is an equivalent to the inlet temperature of that intermediate expansion turbine.
  • the method comprises obtaining a pressure ratio over at least one intermediate expansion turbine, and obtaining, in particular calculating or computing, an inlet temperature of said intermediate expansion turbine, or the outlet temperature of a combustion stage arranged immediately upstream said intermediate expansion turbine, wherein obtaining the outlet temperature of the upstream combustion stage comprises further considering the pressure ratio over the intermediate expansion turbine.
  • the method comprises obtaining a pressure ratio over each intermediate expansion turbine and obtaining, in particular calculating or computing, an inlet temperature of an intermediate expansion turbine, or the outlet temperature of a combustion stage arranged immediately upstream an intermediate expansion turbine, respectively, wherein obtaining the outlet temperature of the upstream combustion stage comprises further considering the pressure ratios over all intermediate expansion turbines.
  • the calculation of the outlet temperature of upstream combustion stages is based upon calculating a balance of the enthalpies from the entry into a first, most upstream, combustion stage to the outlet of a last, most downstream, expansion turbine.
  • the enthalpy drop over the expansion turbine can be derived with knowledge of certain thermodynamic characteristics of the specific expansion turbine, and from there the inlet temperature of the expansion turbine can be calculated. This can be done for each expansion turbine in the gas turbine engine.
  • a measurement of the exhaust temperatures of intermediate expansion turbines has shown to be subject to certain limitations. The same applies to a measurement of temperatures between two immediately subsequent combustion stages.
  • the enthalpy added along said flowpath due to combustion can be derived.
  • the fuel massflow to each combustion stage or fuel massflow ratio enables to determine the enthalpy added in each combustion stage.
  • the inventors have discovered that this balance enables the calculation of the temperatures upstream and downstream each combustion stage and furthermore upstream and downstream each intermediate expansion turbine, if present.
  • Information indicative of the temperature downstream the last, most downstream expansion turbine and upstream the first, most upstream combustion stage is sufficient, wherein, as mentioned above, in particular the temperature upstream the first combustion stage may be derived from other values.
  • Embodiments of the herein disclosed method further comprise considering a parameter representative of at least one coolant mass flow in intermediate expansion turbines and/ or the combustion stages and/or between two subsequent combustion stages for the determination of the outlet temperature of the upstream combustion stage.
  • said parameter may be provided as a constant or coefficient in an equation used for calculating said outlet temperature.
  • an intermediate turbine may or may not be provided between the two aforementioned combustion stages. More specifically, also the temperatures of the coolant mass flows may be considered in obtaining, more specifically in calculating or computing, said outlet temperature.
  • the method may further comprise considering at least one parameter representative of a at least one inert fluid mass flow and temperature of an inert fluid injected into the working fluid mass flow of the gas turbine engine in obtaining an outlet temperature of an upstream combustion stage.
  • Said parameter may be measured mass flows and temperatures, but the mass flow may for other, non-limiting instances be provided as control valve positions.
  • the herein disclosed method may comprise considering combustor pressure drops in obtaining the outlet temperature of the upstream combustion stage.
  • the method may comprise further considering the fuel temperature in obtaining, in particular calculating or computing, the outlet temperature of the upstream combustion stage.
  • obtaining the at least one first parameter representative of the inlet temperature of the last expansion turbine and/or the outlet temperature of the last of said combustion stages comprises obtaining an outlet temperature of the last expansion turbine, obtaining a pressure ratio over the last expansion turbine, and at least one parameter representative of the thermodynamic behavior of the last expansion turbine.
  • This per se, is a method well-known to the skilled person and may comprise the so called "TIT formula", which in instances is a polynomial with the outlet temperature of the last expansion turbine and the pressure ratio over the last expansion turbine as variables, and the coefficients representing the thermodynamic characteristics of the last expansion turbine.
  • conditions of the air at the inlet to the compressor may be considered, such as the relative humidity of ambient air.
  • the pressure may at least essentially equal the pressure at the compressor inlet of the gas turbine engine, and may more specifically essentially equal the ambient or atmospheric pressure, with the deviations as outlined above due to pressure losses in an exhaust duct.
  • "essentially equals” is used due to the fact that in view of pressure losses in a fluid passage to the compressor inlet and in an exhaust flow path of the gas turbine engine those values may slightly differ from each other and/or from the ambient pressure.
  • the temperature of the working fluid at the outlet of the last expansion turbine is in most instances reduced to a temperature range, dependent upon the gas turbine type and operating regime, of at most 500°C - 700°C.
  • the pressure and temperature conditions at the outlet of the last expansion turbine allow an unproblematic application of temperature sensors such as for instance thermocouples in the exhaust fluid flow emanating from the last expansion turbine.
  • the at least one first parameter representative of the outlet temperature of the most downstream combustion stage and/or inlet temperature of the most downstream expansion turbine may be obtained by other methods known to or conceivable by a skilled person.
  • Obtaining the at least one second parameter representative of the outlet temperature of the compressor and/or the inlet temperature of the first of the combustion stages may comprise measuring the outlet temperature of the compressor and/or the inlet temperature of the first of the combustion stages as a second parameter.
  • obtaining the at least one second parameter representative of the outlet temperature of the compressor and/or the inlet temperature of the first of the combustion stages comprises measuring a temperature and a pressure upstream of the compressor and a pressure at the outlet of the compressor as second parameters.
  • the pressure and temperature upstream the compressor may be an ambient temperature and ambient pressure.
  • Said ambient measurements may also comprise measurements of the ambient humidity and using the ambient humidity as a further second parameter.
  • the method in said instances may further comprise obtaining the position of the vanes in a variable inlet guide vane row as a further second parameter.
  • This method of deducing the outlet temperature of the compressor or the inlet temperature of the first, most upstream combustion stage from certain other parameters for a given compressor is well-known to the person having skill in the art.
  • the at least one second parameter representative of the outlet temperature of the compressor and/or inlet temperature of the most downstream combustion stage may be obtained by other methods known to or conceivable by a skilled person.
  • a mass flow of a liquid agent may be injected into a mass flow through the compressor upstream of or inside the compressor. Said mass flow of liquid agent may be a further second parameter.
  • Figure 1 shows a first exemplary embodiment of an air-breathing gas turbine engine having two serially arranged combustion stages.
  • the gas turbine engine comprises compressor 10, first or upstream combustion stage 21 and second or downstream combustion stage 22, and expansion turbine 30.
  • Expansion turbine 30 is coupled to compressor 10 by shaft 40 to drive the compressor and further a load, such as for instance a generator, which is not shown in the depiction, but familiar to the person having skill in the art.
  • a load such as for instance a generator, which is not shown in the depiction, but familiar to the person having skill in the art.
  • Each of combustion stages 21 and 22 may independently from each other be supplied with a respective fuel mass flow ⁇ Fuel,1 to the first, upstream combustion stage 21 and ⁇ Fuel,2 to the second, downstream combustion stage 22.
  • Compressor 10 is equipped with a row of variable inlet guide vanes 11 which allow control of the inlet volume flow to compressor 10 and thus of the working fluid mass flow of the gas turbine engine.
  • the position of the variable inlet guide vanes is denoted by VIGV.
  • compressor 11 receives a flow of inlet air 52 at temperature T 0 and pressure p 0 .
  • Pressure p 0 may in common, while non-limiting, instances be at least essentially equal an ambient pressure, apart from potential pressure losses in air filters, silencers and/or other installations in an inlet duct.
  • Compressor 10 compresses the flow of inlet air to a pressure p 1 , which depends on the working fluid mass flow, flow characteristics of expansion turbine 30, the inlet temperature to the turbine and potential further influencing parameters.
  • the pressure p 4 downstream expansion turbine 30 may in non-nonlimiting instances be at least essentially equal to ambient pressure, apart from pressure losses in installations downstream in an exhaust duct, such as tubing of a heat recovery steam generator, scrubbers and so forth.
  • expansion turbine outlet pressure p 4 may at least essentially equal the compressor inlet pressure po, apart from pressure losses in the exhaust duct and in the air intake.
  • expansion turbine 30 is the only expansion turbine of the gas turbine engine, it is at the same time a last, most downstream expansion turbine.
  • second, downstream combustion stage 22 may be referred to as most downstream or last combustion stage.
  • Pressures p 0 , p 1 and p 4 may be readily measured. Pressures p 2 and p 3 may also be obtained through direct measurement, or otherwise be accounted for through known pressure loss characteristics of the combustion stages. However, while temperatures T 0 at the compressor inlet, T 1 at the compressor outlet and T 4 at the outlet of last expansion turbine 30 may be obtained through direct measurement, a reliable measurement of temperatures T 2 and T 3 at the outlets of the combustion stages turns out at least fairly difficult, if not unfeasible in field applications.
  • T 3 at the outlet of the last, most downstream combustion stage 22 based upon the pressure ratio p 3 /p 4 over the last, most downstream expansion turbine 30 and the temperature T 4 at the outlet of the last, most downstream expansion turbine 30 are well-known to the person having skill in the art.
  • the temperature T 3 at the inlet of expansion turbine 30 can be calculated as a function of the temperature T4 at the outlet of expansion turbine 30 and the pressure ratio p 3 /p 4 over the expansion turbine.
  • the temperature T 2 at the outlet of first combustion stage 21, or at the inlet of second combustion stage 22, respectively it may prove highly desirable to obtain reliable information about temperature T 2 at the outlet of first combustion stage 21, or at the inlet of second combustion stage 22, respectively.
  • temperature T 2 at the outlet of the first combustion stage 21, or at the inlet of the second combustion stage 22, respectively is determined and obtained based upon a heat balance between the outlet of compressor 10 and the inlet of expansion turbine 30.
  • temperature T 2 can be calculated based upon a set of measured values and a thermodynamic model of the gas turbine engine, and/or the components thereof, respectively, by an enthalpy balance between the outlet of compressor 10 and the inlet of expansion turbine 30, and over the first and second combustion stages.
  • the fuel mass flows may be considered in the calculations, or computations, respectively, by a fuel massflow ratio, which may, non-limiting, be defined as ⁇ Fuel,1 / ⁇ Fuel,2 .
  • a fuel massflow ratio which may, non-limiting, be defined as ⁇ Fuel,1 / ⁇ Fuel,2 .
  • the skilled person will be readily aware of which other influencing parameters, like coolant mass flows and temperatures and thermodynamic behavior of components, must be additionally considered in obtaining the desired temperatures.
  • the embodiment shown in figure 2 differs from the embodiment discussed above in that an intermediate expansion turbine 31 is fluidly interposed between first combustion stage 21 and second combustion stage 22.
  • Expansion turbine 31 is through shaft 40 mechanically coupled to expansion turbine 30 and compressor 10.
  • a fuel gas mass flow 56 is discharged from the first combustion stage 21 into intermediate expansion turbine 31.
  • the temperature at the outlet of the first combustion stage, or at the inlet of intermediate expansion turbine 31, respectively, is T 21
  • the pressure is p 21 .
  • the working fluid is expanded from pressure p 21 to pressure p 22 , whereby the temperature decreases from T 21 to T 22 .
  • Temperature T 22 and pressure p 22 are the temperature and pressure at the outlet of intermediate expansion turbine 31 and at the inlet of second combustion stage 22.
  • temperatures T 21 at the outlet of the first, upstream combustion stage or the inlet of the intermediate expansion turbine, respectively, and T 22 at the outlet of the intermediate expansion turbine or the inlet of the second, downstream combustion stage can be calculated.
  • the calculation may require recursions.
  • the skilled person will be readily aware of which other influencing parameters, like coolant mass flows and temperatures and thermodynamic behavior of components, must be additionally considered in obtaining the desired temperatures.
  • thermodynamic state of the working fluid can be obtained at the outlet of each combustion stage without the need to place temperature measurement instrumentation in the thermally highly loaded section of the gas turbine engine between the first, most upstream combustion stage and the outlet of the last, most downstream expansion turbine.
  • instrumentation which, in view of the high pressures and temperatures, is potentially subject to high maintenance requirements, can be omitted throughout the entire working fluid flow path from the inlet to the compressor to the outlet of the last, most downstream expansion turbine.
  • potentially unreliable measurements can be avoided to have an impact on engine control, while omitting the instrumentation and the potentially required high maintenance effort reduces cost.
  • the method may be applied in serial combustion gas turbine engines with as well as without an intermediate expansion turbine being fluidly interposed between two combustion stages.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Turbines (AREA)
EP18176673.4A 2018-06-08 2018-06-08 Procédé pour déterminer une température de sortie d'un étage de combustion amont dans un moteur à turbine à gaz comportant au moins deux étages de combustion disposés en série Withdrawn EP3578762A1 (fr)

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Application Number Priority Date Filing Date Title
EP18176673.4A EP3578762A1 (fr) 2018-06-08 2018-06-08 Procédé pour déterminer une température de sortie d'un étage de combustion amont dans un moteur à turbine à gaz comportant au moins deux étages de combustion disposés en série

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EP18176673.4A EP3578762A1 (fr) 2018-06-08 2018-06-08 Procédé pour déterminer une température de sortie d'un étage de combustion amont dans un moteur à turbine à gaz comportant au moins deux étages de combustion disposés en série

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113107675A (zh) * 2021-04-28 2021-07-13 中国航发沈阳发动机研究所 一种基于功率平衡的核心机涡轮前温度确定方法

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0718470A2 (fr) 1994-12-24 1996-06-26 ABB Management AG Procédé d'opération d'une turbine à gaz
EP2385233A1 (fr) * 2010-05-07 2011-11-09 Alstom Technology Ltd Procédé d'exploitation d'une unité de turbine à gaz basée sur la température de la chambre de combustion
US20130239573A1 (en) * 2012-03-19 2013-09-19 Alstom Technologies Ltd Method for operating a combined cycle power plant and plant to carry out such a method
US20130269362A1 (en) * 2012-04-12 2013-10-17 General Electric Company Methods, systems and apparatus relating to combustion turbine power plants with exhaust gas recirculation
US8794008B2 (en) * 2009-04-01 2014-08-05 Alstom Technology Ltd Methods of operation of a gas turbine with improved part load emissions behavior
EP3267107A1 (fr) * 2016-07-08 2018-01-10 Ansaldo Energia IP UK Limited Procédé de commande d'un ensemble de turbine à gaz

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0718470A2 (fr) 1994-12-24 1996-06-26 ABB Management AG Procédé d'opération d'une turbine à gaz
US8794008B2 (en) * 2009-04-01 2014-08-05 Alstom Technology Ltd Methods of operation of a gas turbine with improved part load emissions behavior
EP2385233A1 (fr) * 2010-05-07 2011-11-09 Alstom Technology Ltd Procédé d'exploitation d'une unité de turbine à gaz basée sur la température de la chambre de combustion
US20130239573A1 (en) * 2012-03-19 2013-09-19 Alstom Technologies Ltd Method for operating a combined cycle power plant and plant to carry out such a method
US20130269362A1 (en) * 2012-04-12 2013-10-17 General Electric Company Methods, systems and apparatus relating to combustion turbine power plants with exhaust gas recirculation
EP3267107A1 (fr) * 2016-07-08 2018-01-10 Ansaldo Energia IP UK Limited Procédé de commande d'un ensemble de turbine à gaz

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113107675A (zh) * 2021-04-28 2021-07-13 中国航发沈阳发动机研究所 一种基于功率平衡的核心机涡轮前温度确定方法

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