Thermal picture giving system for a turbine.

Background to the invention the article revealed herein concerns a thermal picture giving system for a turbine. Certain gas turbines contain a turbine, which exhibits view openings, which are configured, in order to make a monitoring possible different components within the turbine. For example a Pyrometriesystem can receive radiation signals by the view openings, in order to measure the temperature of certain components within a hot gas path of the turbine. The Pyrometriesystem knows a sensor, which is configured within a Infrarotspektrums for the measurement of a radiation, and control equipment contain, which is configured to convert around the radiation measurement into a temperature map of the components. Regrettably fluctuations of the Emissivität of the components can affect the temperature computation disturbing. For example the Emissivität in the course of the time can vary due to temperature changes, arrears deposits on the components, an oxidation of turbine components and/or an accumulation of dirt at the sight. Therefore the use from infrared measurements can bring inaccurate temperature maps out of the components to the computation of the temperature in certain cases. In addition a camera with a short average time can be used, in order to take up pictures the components due to the high-speed rotation of certain turbine components (e.g. turbine rotor blades). For example cameras with an average time can be used from approximately 1 microsecond, in order to take up pictures of turbine rotor blades, which rotate with approximately 50 cycles per second. The short average time makes possible for the camera to take up pictures with high spatial resolution. Regrettably such cameras can be very expensive. Short description of the invention in an execution form contains a system a picture giving system, which is configured, in order to communicate in optical way with an interior of a turbine. The picture giving system contains at least one camera, which is configured, in order to take up and spend around signals several pictures in the visible spectrum of a circulating component inside the turbine, which mark a two-dimensional intensity profile of each picture in the visible spectrum. Furthermore the picture giving system contains control equipment, which is connected with that at least to a camera communication-moderately and configured, in order to determine a two-dimensional temperature map of the circulating component on the basis of the signals. In a further execution form a system contains a picture giving system, which is configured to take up in order to take up a first picture of a circulating component inside a turbine with a first average time, a second picture differs the circulating component inside the turbine with a second average time which from the first average time, and the first picture from the second picture to subtract, in order to receive a difference picture. In a further execution form a system contains a picture giving system, which is configured, in order to communicate with an interior of a turbine optically. The picture giving system contains a camera, which is configured, in order to spend a picture in the visible spectrum of a component inside the turbine too received and around signals, which mark a two-dimensional intensity profile of the picture in the visible spectrum. Furthermore the picture giving system contains control equipment, which is coupled with the camera communication-moderately and configured, in order to determine a two-dimensional temperature map of the component on the basis of the signals. Short description of the designs [of 0007] these and further characteristics, aspects and advantages of the available invention are understood better, if the following detailed description with reference to the attached designs is read, in which same reference symbols everywhere in the designs same parts represent, where show: Fig. 1 a block diagram of an execution form of a turbine system, which contains a picture giving system, which is configured, in order to determine a two-dimensional temperature map of a turbine component on the basis of a picture in the visible spectral region and/or to compute a difference picture of the component with high spatial resolution; Fig. 2 a cross section opinion of an exemplary turbine section under illustration of different turbine components, which can be supervised by an execution form of the picture giving system; Fig. 3 a schematized representation of an execution form of the picture giving system by control equipment, which is configured, in order signals to receive, which a picture in the visible spectrum of a turbine component mark, and in order a two-dimensional temperature map on the basis of the signals to determine; and CH 704417 a2 Fig. 4 a schematized representation of an execution form of a picture giving system, which exhibits control equipment, which is configured, in order to compute a difference picture of a turbine component on the basis first and a second picture, which exhibit another average time in each case. Detailed description of the invention one or more special execution forms are below descriptive. In the tendency to supply a briefly seized description of these execution forms not all characteristics of an actual realization can be descriptive if necessary in the description. It should be understood that with the emergence of each such actual realization, like in each Ingenieursoder construction project, numerous realization-specific decisions to be met to have, in order to achieve the special goals of the developers as for example the adherence to system related and enterprise-referred restrictions of edge, which can vary from a realization to the other one. In addition that such developping costs can be complex and time-consuming, however nontheless for specialists with usual expertise, which has the use of this revealing, a routine venture should be recognized for the construction, manufacturing and production would represent. If elements of different execution forms, which are revealed herein, are introduced, the articles are to mean “”, “one”, “”, “” and “” that there are or several of the elements. The expressions “exhibit”, “contained” and “” were be inclusive and mean that there can be further elements except the specified elements. Herein revealed execution forms can make improved temperature measurements and/or pictures possible with higher spatial resolution of turbine components. In an execution form is a picture giving system configures, in order to communicate with an interior of a turbine optically. The picture giving system contains at least one camera, which is configured, in order to take up and spend around signals several pictures in the visible spectral region of a circulating component inside the turbine, which mark a two-dimensional intensity profile of each picture in the visible spectral region. Furthermore the picture giving system contains control equipment, which is connected with that at least to a camera communication-moderately and configured, in order to determine on the basis of the signals a two-dimensional temperature map of the circulating component. Because the two-dimensional temperature map is based on a picture in the visible spectrum, the computed temperatures can be more exact within the temperature map than the temperatures computed from pictures in the Infrarotspektrum. In particular temperature computations, which are based on emissions in the visible wavelength coverage, depend less on fluctuations of the Emissivität than on infrared radiation which are based computations. Therefore the control equipment supplies exact temperature maps despite an arrears deposit at the circulating component, to an oxidation with of the circulating component and/or an accumulation of dirt at a sight. The difference picture can exhibit a spatial dissolution, which is essentially similar to a picture with an average time, which corresponds to the difference between the first average time and the second average time. Because cameras, which are able to work with longer average times are clearly more economical than cameras, which can work at shorter average times, the picture giving system can result in an economically justifiable system for the production of pictures with high spatial resolution. As now to the designs is referred, figure 1 shows a block diagram of an execution form of a turbine system, which contains a picture giving system, which is configured, in order to determine a two-dimensional temperature map of a turbine component on the basis of a picture in the visible spectrum and/or to compute a difference picture of the component with high spatial resolution. The turbine system 10 contains a fuel injector 12, a fuel a supply 14 and a combustion chamber 16. How illustrates, the fuel supply 14 leads a liquid fuel and/or a gaseous fuel, as for example natural gas, to the gas turbine system by the fuel injector 12 through into the combustion chamber 16 inside. As describes below, the fuel injector is 12 configures, in order to inject and mix with compressed air the fuel. The combustion chamber 16 ignites and burns the fuel air mixture and leads is called under pressure standing exhaust gases of far to a turbine 18. As is understood, the turbine 18 contains one or more stators with stationary guide vanes or shovels as well as one or more rotors with shovels, which rotate relative to the stators. The exhaust gas passes the turbine rotor blades, whereby the Turbinenrotor is turning propelled. A coupling between the Turbinenrotor and a wave 19 arranges the turn of the wave 19, which is coupled furthermore with different components everywhere in the gas turbine system 10, as this is illustrated. Finally the exhaust gas can withdraw from the burn process from the gas turbine system 10 over an exhaust discharge opening 20. A compressor 22 contains rotor blades, which are rigidly installed at a rotor, which is propelled by the wave 19 turning. If air passes the rotary rotor blades, the air pressure rises, whereby the combustion chamber will provide 16 with sufficiently air for normal burn. The compressor 22 can take up air to the gas turbine system 10 over an air intake 24. Furthermore the wave can be coupled 19 with a load 26, which can be propelled over a CH 704417 a2 a turn of the wave 19. As is recognized, the load 26 can be any suitable device, which can use the achievement of the turning expenditure of the gas turbine system 10, as for example an energy production plant or an external mechanical load. For example the load 26 can contain an electrical generator, a propeller of an airplane and such a thing. The air intake 24 draws air 30 into the gas turbine system 10 over a suitable mechanism, as for example a cool air inlet. Air 30 moves by afterwards at the rotor blades of the compressor 22, which supplies compressed air 32 to the combustion chamber 16. In particular the fuel injector 12 can inject compressed air 32 and the fuel 14 as a fuel air mixture 34 into the combustion chamber 16. Alternatively compressed air 32 and the fuel 14 can be injected for the mixture and burn directly into the combustion chamber. As illustrates, the turbine system 10 contains a picture giving system 36, which is optically coupled with the turbine 18. In the illustrated execution form the picture giving fig. 36 contains an optical connection 38 (e.g. an optical waveguide cable, a fibre optics, etc.), which extends between a view opening 40 to the turbine 18 and a camera 42. As describes below in details, the camera 42 is configures, in order to receive a two-dimensional picture in the visible spectrum of a component inside the turbine 18 by the view opening 40 through. The camera 42 is communication-moderately coupled with control equipment 44, which is configured, in order to determine a two-dimensional temperature map of the component on the basis of the picture in the visible spectrum. Because the two-dimensional temperature map is based on a picture in the visible spectrum, the computed temperatures can be more exact in the temperature map than temperatures, which are computed from pictures in the Infrarotspektrum. The difference picture can exhibit a spatial dissolution, which is essentially similar to a picture with an average time, which is equal to the difference between the first average time and the second average time. Because cameras, which can work with longer average times, are clearly more economical than cameras, which can work with shorter average times, the picture giving system can create an economically practicable system for the production of pictures with high spatial resolution. Fig. a cross section opinion of a turbine section, which illustrates different turbine components, shows 2, which can be supervised by the picture giving fig. 36. How illustrates, the exhaust gas 48 out of the combustion chamber 16 into the turbine 18 inside in an axial direction 50 flows and/or a circumferential direction 52. The illustrated turbine 18 contains at least two stages, whereby the first two stages in Fig. 2 is illustrated. Other turbine configurations can contain several or few turbine stages. For example a turbine can contain 1.2, 3, 4, 5, 6 or several turbine stages. The first turbine stage contains guide vanes 54 and rotor blades 56, which are essentially evenly beabstandet arranged in the circumferential direction 52 of ring around the turbine 18. The guide vanes 54 of the first stage are installed at the turbine 18 rigidly and configure, in order to steer incineration gases in the direction of the rotor blades 56. The rotor blades 56 of the first stage are installed at a rotor 58, which is propelled by the exhaust gas 48, which to the run 56 digs flows past, turning. The rotor 58 is again coupled with the wave 19, which propels the compressor 22 and the load 26. The exhaust gas 48 flows afterwards at guide vanes 60 of the second stage and run digs 62 for the second stage past. The rotor blades 62 of the second stage are likewise coupled with the rotor 58. While the exhaust gas 48 flows by each stage, energy from the gas is converted into rotational energy of the rotor 58. After passing each turbine stage withdraws the exhaust gas 48 from the turbine 18 in the axial direction 50. In the illustrated execution form each guide vane 54 of the first stage of a Endwand 64 in a radial direction 66 extends outward. The Endwand 64 is configures, in order to prevent the hot exhaust gas 48 from entering the rotor 58. A similar Endwand can be present neighbouring to the guide vanes 60 of the second stage and, if they are present, following stromabwärtigen guide vanes. In similar way each Laufschaufe156 of the first stage of a platform 68 out in the radial direction 66 extends outward. As is recognized, the platform 68 is a part of a shank 70, which couples the Laufschaufe156 with the rotor 58. Furthermore the shank 70 contains a poetry or a Engelflüge172, which is configured and/or, in order to prevent the hot exhaust gas 48 from entering the rotor 58. Similar platforms and angel wing can be present neighbouring to the rotor blades 62 of the second stage and, if they are present, following stromabwärtigen rotor blades. In addition a coat 74 radially outside positioned from the rotor blades 56 of the first stage is. The coat 74 is configures, in order to reduce the quantity of the exhaust gases 48, which flow around the rotor blades 56, to a minimum. A gas bypass is unwanted, because energy from the flowing around gas is seized by the rotor blades 56 and is not converted not in rotational energy. While execution forms of the picture giving fig. 36 are descriptive below with reference to monitoring components within the turbine 18 of a gas turbine 10, that the picture giving fig. 36 can be used, in order components within other rotary and/or hinund moved machines, as for example a turbine, in that steam or another work fluid turbine rotor blades should be recognized happened, to supervise. As is recognized, different components are exposed a2 exhaust gas 48 from the combustion chamber 16 to the hot CH 704417 within the turbine 18 (e.g. the guide vanes 54 and 60, the run dig 56 and 62, the Endwände 64, the platforms 68, the angel wings 72, the coats 74, etc.). Therefore it can be desired to measure a temperature of certain components during the enterprise of the turbine 18 to supervise in order to guarantee that the temperature remains within a desired range, and/or in order thermal stress within the components. For example the picture giving fig. 36 can configures to be, in order to take up a two-dimensional picture in the visible spectrum of the turbine rotor blades 56 of the first stage. The two-dimensional picture in the visible spectrum can be used afterwards, in order to compute a two-dimensional temperature map of the surface of the rotor blades 56. Because the two-dimensional temperature map is based on a picture in the visible spectrum, the computed temperatures can be more exact within the temperature map than temperatures, which are computed from pictures in the Infrarotspektrum. As illustrates, the picture giving system contains 36 three view openings 40, which are arranged to different ranges of the rotor blade 56. Three optical connections 38 couple the view openings 40 optically with the camera 42. A first optical connection 76 is configures to convey in order to convey a picture of a stromaufwärtigen section of the rotor blade 56 to the camera 42, while a second optical connection 78 is configured, in order a picture from an extent side of the rotor blade 56 to the camera 42 and a third optical connection configures is, in order to convey a picture of a stromabwärtigen section of the rotor blade 56 to the camera 42. The view openings 40 can be arranged in the axial direction 50, the circumferential direction 52 and/or the radial direction 66 under an angle, in order to align the view openings 40 in the direction of the desired ranges of the rotor blade 56. In alternative execution forms several or few view openings 40 and optical connections 38 can be used, in order to receive pictures from the rotor blade 56 of the first stage. For example some execution forms 1.2, 3, 4, 5, 6, 7, 8 or several view openings 40 and an appropriate number of optical connections 38 can use, in order to transfer pictures from the rotor blade 56 to the camera 42. It could be supervised recognized that the more view openings 40 and optical connections 38 are used, the more ranges of the Laufschaufe157. As describes managing, the optical connections 38 know for example an optical waveguide cable or a fibre optics contain. Furthermore it should be recognized that certain execution forms can omit the optical connections 38 and the camera 42 can be directly optically coupled with the view openings 40. While the view openings 40 in the illustrated execution form to the rotor blades 56 of the first stage are arranged, it should be recognized that the view openings 40 can be directed in alternative execution forms to other turbine components. For example can know/one or more view openings 40 to the guide vanes 54 of the first stage, the guide vanes 60 of the second stage, the rotor blades 62 of the second stage, the Endwänden 64, the platforms 68, the angel wings 72, the coats 74 or other components within the turbine 18 be arranged. Furthermore execution forms can contain view openings 40, which can be directed to several components within the turbine 18. Similarly the rotor blades 56 of the first stage the picture giving fig. 36 can a two-dimensional picture in the visible spectrum of each component within a field of view of a view opening 40 seize and on the basis of the picture in the visible spectrum a two-dimensional temperature map determine. In this way an operator can identify easily excessive variations in temperature over the component and/or defects (e.g., cooling holes, etc. blocked tears) within the turbine component. As describes managing, the optical connections 38 (e.g. optical waveguide cable, fibre optics, etc.) transfer a picture from the turbine 18 to the camera 42. The camera 42 can configures to be, in order to take up several pictures over a length of time away. As is recognized, certain turbine components, as for example the rotor blades 56 of the first stage, can rotate as managing described, with high number of revolutions along the circumferential direction 52 of the turbine 18. Therefore the camera 42 can, in order to take up a picture of a such component, configures to be, in order to work at an average time, which is sufficient, in order to essentially supply to the control equipment 44 a quiescent picture from each component to. For example the camera 42 in some execution forms knows configures to be, in order to spend the visible picture of the turbine component characteristic signal with an average time, which is shorter than about 10, 5, 3, 2, 1 or 0.5 microseconds or less. Alternatively can the control equipment configures to be to subtract in order to take up a first picture in the visible spectrum of the circulating component using a first average time to take up a second picture in the visible spectrum of the circulating component using a second average time which differs from the first average time, and the first picture in the visible spectrum of the second picture in the visible spectrum in order to receive a difference picture. The difference picture can exhibit a spatial dissolution essentially similarly a picture with an average time, which is equal to the difference between the first average time and the second average time. Because cameras, which are able to work with longer average times are clearly more economical than cameras, which are able to work with shorter average times the picture giving system can result in an economically justifiable system for the production of pictures with high spatial resolution. In some execution forms the optical, connections can be coupled 38 with a multiplexer within the camera 42, in order to make a Uberwachung possible of pictures from each point of observation. As is recognized, pictures can be gemultiplext by each optical connection 38 spatially or temporally. If for example the multiplexer is configured, around the pictures spatially to multiplex, each picture on another section of a picture version device (e.g. a charge-coupled construction unit (CCD, load coup LED DEVICE), a complementary MetalI oxide semiconductor (CMOS), etc.) can be projected within the camera 42. In this configuration a picture of CH can be directed 704417 a2 of the first optical connection 76 toward an upper section of the picture version device, while a picture can be directed by the second optical connection 78 toward a central section of the picture version device and a picture can be arranged by the third optical connection 80 in the direction of a lower section of the picture version device. Consequently the picture version device knows each picture with a dissolution of a third scanning. In other words the Scannauflösung is in reverse proportional to the number of spatially gemultiplexter signals. As is recognized, Scanns of smaller dissolution supply fewer information about the turbine component to the control equipment 44 than Scanns with higher resolution. Therefore the number of spatially gemultiplexter signals can be limited by the minimum dissolution, which is sufficient for the control equipment 44, in order to produce a desired two-dimensional picture from the turbine component to. Alternatively pictures, which are supplied by the optical connections 38, can be gemultiplext temporally. For example the camera 42 knows alternating a picture of each optical connection 38 with the entire dissolution of the picture version device scanning. Using this technology the full dissolution of the picture version device can be used, whereby however the Scannfrequenz can be reduced proportionally to the number of scanned points of observation. If for example two points of observation become strained and the frequency of the picture version fig. 100 cycles per second amounts to, the camera is 42 only able, pictures of each point of observation with 50 cycles per second to scanning. Therefore the number of temporally gemultiplexter signals can be limited by the desired Scannfrequenz. Fig. a schematic shows 3 representation of an execution form of the picture giving system, which exhibits control equipment, which is configured, in order signals to receive, which a picture in the visible spectrum of a turbine component, mark, and in order a two-dimensional temperature map on the basis of the signals to determine. As illustrates, the camera 42 arranged to a turbine rotor blade 56 of the first stage is. However it should be recognized that the camera 42 in alternative execution forms in the direction of other turbine components (e.g. the guide vanes 54 and 56, rotor blades 62, Endwände 64, platforms 68, angel wing 72, coats 74, etc.) to be arranged knows. In addition several cameras 42 can be used in alternative execution forms. For example can be arranged in some execution forms 1, 2, 3, 4, 5, 6, 7, 8 or several cameras 42 in the direction of the rotor blade 56. As describes managing, further execution forms can contain several optical connections 38, which extend between the turbine 18 and a multiplexer in each camera 42. In the illustrated execution form the camera 42 is configures, in order to spend a picture in the visible spectrum of the turbine rotor blade 56 too received and around signals to the control equipment 44, which mark a two-dimensional intensity profile 82 of the picture in the visible spectrum. For example the camera 42 can contain a picture version device, which is sensitive within the visible spectral region for a radiation. A such picture version device knows configures to be, over visible radiation, which is emitted and reflected by the turbine components to convert into an electrical signal for processing by the control equipment 44. As is recognized, the picture version device can be a charge-coupled device (CCD), complementary metal oxide semiconductor (CMOS), one as Focal tarpaulin array (FPA, fuel level array suitable of radiation detectors or) characteristic two-dimensional arrangement any other device for the transformation of an electromagnetic radiation in the visible spectral region into electrical signals. In some execution forms can the picture version device configures to be, in order to seize a radiation in the visible spectrum within a wavelength coverage from for example about 350 Nm to approximately 750 Nm, about 375 Nm to approximately 725 Nm or about 400 Nm to approximately 700 Nm. The spectral content accordingly contains a radiation of the two-dimensional intensity profile 82 within the visible range of the electromagnetic spectrum. In addition it should be recognized that various camera configurations can be used, in order to take up the picture in the visible spectrum of the turbine component. For example a consumer-fair digital mirror reflex camera (SLR camera) can be used, in order to take up and spend around signals to the control equipment 44 the picture in the visible spectrum in some execution forms, which mark the two-dimensional intensity profile 82 of the picture in the visible spectrum. SLR cameras contain a reflex mirror, which turns into alternatively between a first position, which steer arriving light to an eyepiece, and a second position, which steer the arriving light to the picture version device. In this configuration an operator can use the eyepiece, in order to arrange the SLR camera in the direction of a desired goal (e.g. the Turbinenlaufschaufe156). As soon as it is aligned, the SLR camera can be activated, whereby the reflex mirror changes into the second position and is made possible for the picture version device to take up the picture in the visible spectrum. As is recognized, alternative execution forms can use other camera configurations, which do not contain the reflex mirror or the eyepiece. As illustrates, the signals, which mark the two-dimensional intensity profile 82, are conveyed to the control equipment 44. As describes managing, the control equipment 44 is configures, in order to determine on the basis of the signals a two-dimensional temperature map of the component (e.g. the turbine rotor blade 56). In the illustrated execution form is the control equipment configures, in order to isolate the two-dimensional intensity profile 82 computationally into several intensity profiles with narrow wavelength volume. For example the control equipment 44 can do configures to be, in order to divide the intensity profile 82 in a red intensity profile 84, a green intensity profile 86 and a blue intensity profile 88. In a such configuration the red intensity profile can contain 84 wavelengths in a range from approximately 600 Nm to approximately 750 Nm, while the green intensity profile can contain 86 wavelengths CH 704417 a2 within a range from approximately 475 Nm to approximately 600 Nm and the blue intensity profile can contain wavelengths within a range from approximately 400 Nm to approximately 475 Nm. Alternative can contain the two-dimensional intensity profile of 82 characteristic signals red, Grünund blue components according to respective detectors within the picture version device. In the illustrated execution form the control equipment is 44 configures, in order to compute on the basis WellenIängenschmalband lntensitätsprofile two-dimensional temperature maps. As illustrates, the control equipment 44 contains a first temperature conversion curve 90, which is configured, in order to illustrate the intensity of each pixel within red lntensitätsprofils 84 on an associated temperature. Also the control equipment 44 contains a second temperature conversion curve 92 for green lntensitätsprofil of 86 and a third temperature conversion curve 94 for blue lntensitätsprofil 88. While each temperature conversion curve is illustrated as a continuous curve, it should be recognized that the control equipment 44 can use empirical formula, look-up table, interpolation system (e.g. linear interpolation, smallest squares, cubic Spline, etc.) or another method for the illustration of the intensity of each pixel on an appropriate temperature. Therefore the control equipment 44 produces a first two-dimensional temperature distribution 96 on the basis red lntensitätsprofils 84, a second two-dimensional temperature distribution 98 on the basis green lntensitätsprofils for 86 and a third two-dimensional temperature distribution 100 on the basis blue lntensitätsprofils 88. The control equipment 44 can average anschliessend each temperature distribution, in order to produce an output temperature map 102. Because the temperature map 102 is based on an average of the three colors, the temperature map can contain 102 more exact temperatures than on individual colors which are based temperature maps. While in the illustrated execution form three temperature distributions are averaged, it should be recognized that in alternative execution forms several or few temperature distributions can be used. Alternative can be averaged two of the three illustrated temperature distributions (e.g. first and the second temperature distribution 96 and 98), in order to produce the output temperature map 102. In further execution forms the control equipment 44 can configures to be, in order to isolate and generate around temperature distributions on the basis of each intensity profile the two-dimensional intensity profile 82 in 4, 5, 6, 7, 8, 9, 10 or several intensity profiles with narrow wavelength volume. In such execution forms can over all or a selected part of the temperature distributions be averaged, in order to create the output temperature map 102. In other execution forms the control equipment 44 can configures to be, in order to use multi-wavelength techniques, in order to generate the output temperature map 102. As is understood, the Emissivität in the course of the time can due to changes of the temperature, the deposit of arrears on the components, which oxidation of turbine components and/or the accumulation of dirt at the sight vary. Therefore the control equipment 44 can configures to be, in order to use multi-wavelength techniques in combination with the red, Grünund blue intensity profile, in order to compute an obviously effective Emissivität of the turbine component. By admission of the Emissivität into the temperature map computations a more exact temperature map can be generated. Because the illustrated execution form uses a camera 42, which is sensitive for visible radiation, the picture giving system can have more economical to be manufactured 36 than picture giving systems, which use infrared cameras. For example the camera 42, as managing described, can be a digital SLR camera of the consumer quality. A such camera can be clearly more economical than a camera, which is sensitive for infrared radiation. Ausserdem can have the digital SLR camera a clearly higher resolution than an infrared camera, whereby one makes possible for the picture giving fig. 36 to detect smaller defects and/or variations in temperature within the turbine component. Furthermore temperature computations, which are based on visible wavelength emissions, hang less from Emissivitätsschwankungen than computations, which are based on infrared radiation. Therefore the computed temperatures can be more exact within the temperature map 102 than temperatures, which are based on forming infrared cameras. Fig. a schematic representation of an execution form of the picture giving fig. 36, which exhibits control equipment 44, which is configured shows 4, in order to compute a difference picture of a turbine component on the basis first and a second picture, which exhibit another average time in each case. As illustrates, a first camera 104 and a second camera 106 are arranged in the direction of a Turbinenlaufschaufe156 of the first stage. The first camera 104 is configures to take up in order to take up a first fig. 108 using a first average time tl, while the second camera 106 is configured, in order a second fig. 110 using a second average time t2. As is recognized, the average time can be defined as the duration of the photocopy of the turbine component on the picture version device. Due to the high number of revolutions of certain turbine components (e.g. the CH 704417 a2 turbine rotor blades 56) a short average time can be desired, in order to produce a picture with high spatial resolution (e.g. a sharp picture, an identification of tiny characteristics made possible). For example an average time can be used from 1 microsecond, in order to achieve a spatial dissolution of 500 micrometers within a picture of a turbine rotor blade rotating with 50 cycles per second. Regrettably can due to the costs, which are connected with cameras, which exhibit average times of 1 microsecond, picture giving systems, which use such cameras, for a turbine component monitoring economically untenable its. Therefore the illustrated picture giving fig. can use 36 cameras 104 and 106 with longer average time lasting and control equipment 44, which are configured, in order to produce on the basis several pictures with long average time a picture with high spatial resolution. In illustrated execution form is control equipment 44 configures, in order first fig. 108, which first average time tl exhibits, and which second fig. 110, which exhibits the second average time t2, which is longer than the first average time tl, to receive. The control equipment 44 is furthermore configures, in order to subtract the first fig. 108 from the second fig. 110, in order to produce by it a difference picture 112 with a spatial dissolution, which a picture with an average time of t2 - tl is essentially similar. For example the first fig. 108 can have an average time of 49 microseconds, and which can have second fig. 110 an average time of 50 microseconds. Such average times can produce pictures with spatial dissolutions, which are insufficient for the identification of defects within the turbine rotor blades 56. By subtraction of the first fig. 108 of the second picture the control equipment 44 produces however a difference picture 112, which exhibits a spatial dissolution, which is essentially similar to a picture with an average time of 1 microsecond (i.e. 50 microseconds minus 49 microseconds). Therefore the fig. 112 can exhibit a spatial dissolution of 500 micrometers, whereby one makes possible for an operator or an automatic system, defects (e.g. tears, blocked cooling holes, etc.) within the turbine component to identify. Because cameras, which are able to work with average times from approximately 50 microseconds to are clearly more economical than cameras, which are able to work at average times from 1 microsecond to the illustrated picture giving fig. 36 can result in an economically justifiable system for the production of pictures with high spatial resolution. While the control equipment 44 is configured in the illustrated execution form to apply in order to subtract first and the second picture directly, that the control equipment can be configured, in order a weighting factor, either linear or nonlinear weighting factor, to one that or both pictures before subtraction should be recognized. In addition it should be recognized that, while in the illustrated execution form two cameras 104 and 106 are used alternative execution forms can use only one camera, in order to produce first and the second picture. For example can the camera configures to be, in order to take up the first picture, if the turbine rotor blade 56 at a certain extent position is arranged. The camera can take up anschliessend the second picture of the same turbine rotor blade 56, while the turbine rotor blade passes the certain extent position during a following turn. Similarly the configuration with two cameras is the first average time of the first picture different than the second average time of the second picture, whereby is made possible for the control equipment 44 to produce a difference picture with high spatial resolution. For example the spatial dissolution of the difference picture of a spatial dissolution of a picture can be essentially similar, which exhibits an average time, which is equal to the difference between the first average time and the second average time. Ausserdem should be recognized that the control equipment 44 can determine a two-dimensional temperature map 102 of the turbine component on the basis of the difference picture 112. The control equipment 44 can average anschliessend the respective temperature distributions, in order to produce the two-dimensional temperature map of the turbine component. The combination of an exact temperature map and a high spatial resolution makes possible for an operator or automated system to identify defects within the component and/or identify temperature distributions, which let schliessen on a übermässigen wear. This written description uses examples to convert in order to reveal and also over for each specialist possible on the area make the invention, einschliesslich the best type, the invention to which the creation and use of any devices or systems and the execution of any contained procedures belong. The patentable range of the invention is defined by the requirements and can contain further examples, which occur to specialists in the area. Such further examples should be contained to the extent of the requirements, if they exhibit structural elements, which do not differ from the sense of word of the requirements, or if equivalent structural elements contain them also in relation to the sense of word of the requirements insignificant differences. In an execution form a system 10 contains a picture giving fig. 36, which is configured to take up in order to take up a first fig. 108 of a circulating component 56 in an interior of a turbine 18 using a first average time, a second fig. 110 differs the circulating component 56 in the interior of the turbine 18 using a second average time, which from the first average time, and to subtract the first fig. 108 from the second fig. 110, in order to receive a difference picture 112. CH 704417 a2 reference symbol list gas turbine system 12 fuel injector 14 fuel supply 16 combustion chamber 18 turbine 19 wave exhaust discharge opening of 22 compressors 24 inlet 26 load air 32 compressed air 34 fuel air mixture 36 picture giving fig. 38 optical connection view opening, sight 42 camera 44 control equipment 48 exhaust gas axial direction 52 circumferential direction 54 guide vane of the first stage 56 rotor blade of the first stage 58 Turbinenrotor guide vane of the second stage 62 rotor blade of the second stage 64 Endwand 66 radial direction 68 platform shank of 72 angel wings 74 turbine coat 76 first optical connection 78 second, optical connection CH 704417 a2 third optical connection 82 two-dimensional intensity profile 84 red lntensitätsprofil 86 G rün i ntensitätsprofil 88 blue i ntensitätsprofil first Temperatu ru msetzu ngskurve 92 second temperature conversion curve 94 third temperature conversion curve 96 first two-dimensional temperature distribution 98 second two-dimensional temperature distribution third two-dimensional temperature distribution 102 temperature map 104 first camera 106 second camera 108 first picture with first average time second picture with second average time 112 difference picture