Abstract:
The invention refers to a stationary gas turbine arrangement with at least one turbine stage that includes at least a first row of vanes being mounted at a stationary component arranged radially outside of the first row of vanes and extending radially into an annular entrance opening of the turbine stage facing a downstream end of a combustor. Further a method for performing maintenance work on a stationary gas turbine is described. The invention is characterized in that the stationary component provides for each vane a radially orientated through-hole designed and arranged for a radial insertion and removal of the vane, and each of said vanes comprises an airfoil having at its one end directed radially outwards a contour being adapted to close the through-hole airtight by a detachable fixation means.

Description:
CROSS-REFERENCE TO RELATED APPLICATIONS 
     This application claims priority to European Application 12178536.4 filed Jul. 30, 2012, the contents of which are hereby incorporated in its entirety. 
     TECHNICAL FIELD 
     The present invention relates to the field of stationary gas turbine arrangement with at least one turbine stage comprising at least a first row of vanes being mounted at a stationary component arranged radially outwards of the first row of vanes and extending radially into an annular entrance opening of the turbine stage facing a downstream end of a combustor. 
     BACKGROUND OF THE INVENTION 
     A typical stationary gas turbine arrangement provides a burner with a combustor in which hot gases are produced which flow into a turbine stage in which the hot gases performing expansion work. The turbine stage consists of a rotary shaft on which a multitude of blades are arranged and grouped in axially blade rows. The rotary unit is encapsulated by a stationary casing on which vanes are mounted which are also divided in axial distributed vane rows each extending between the blade rows. For performing maintenance work on a typical stationary gas turbine, it is necessary to lift the uppercasing half of the turbine stage to get access to the rotary unit. In most of the cases, it is unavoidable to remove also the rotary unit from the lower casing half for further disassembling work. It is a matter of fact that maintenance work on conventional stationary gas turbines is time and cost consuming which is a significant disadvantage for the gas turbine operating company. 
     Basically it is known that for inspection work inside the outer casing of a turbine stage so called manholes are integrated, so that worker person can gain access to the inner core of the stationary components of the first turbine stage. However, it is not possible to get a direct access to the vanes or blades extending inside the turbine stage because the stationary components, which carry the blades divided in several axially blade rows are typically manufactured in one piece having an axial extension of the length of the turbine stage. In  FIG. 2 , a rough sketch illustrates a longitudinal section view through the first stage gas turbine in the region of the first vane  1  and blade  2 . Hot gases  3 , which are produced inside a combustor  4  flow through the funnel shaped entrance opening  5  of a first turbine stage  6 . Hot gases  3  pass in axial direction through circumferential interspaces between the blades  1 , which are arranged circumferentially around the rotor axis  7  of the rotor unit  8 . Each vane  1  provides a radial outer platform  9 , an airfoil  1 ′ and a radial inner platform  10 . The radial outer platform  9  contains mounting hooks  11 , which are inserted into mounting groves  12  of the stationary component  13  of the first turbine stage. The inner platform  10  of vane  1  typically encloses a gap  14  with the inner combustor liner  15  through which a purge flow of cooling medium  16  can be injected into the hot gas flow  3 . In the same way a purge flow of cooling medium  16 ′ is injected through a gap  14 ′ that is enclosed by parts of the stationary component  13 , the upstream edge of the platform  9  of vane  1  and the outer combustor liner  15 ′. Downstream the outer platform  9  a heat shield  9 ′ is mounted inside of the stationary component  13  which prevents overheating of the inner faced areas of the stationary component in the same way as in case of the outer platform  9 . 
     EP 2 447 475 A2 discloses an airfoil attachment arrangement in which the airfoil  46  is mounted between an outer and inner platform  48 ,  50 . For mounting and demounting purposes in the outer platform  50 , an aperture  90  is processed through which the airfoil can be moved radially. Also at the inner platform  48 , (see  FIG. 11 ) there is an opening (see  FIGS. 11 to 13 ) through which the radial inner end of the airfoil  46  penetrates partially. Both ends of the airfoil  46  are fixed by retention assemblies.  FIGS. 4 and 5  show a retention assembly  54  for fixing the radial outward end of the airfoil  46 .  FIG. 12  shows a retention assembly  126  for fixing the radially inner end of the airfoil  46 . 
     U.S. Pat. No. 6,189,211 B1 discloses a method and arrangement for carrying out repair and/or maintenance work in the inner casing of a multi-shell turbo machine. For getting access to the vanes of the first row a man hole  21  is provided within the outer casing of the gas turbine plant. For getting access to the row of vanes, the top part of the combustion chamber casing  12  can be lifted off by a lifting device  33  as disclosed in  FIG. 2 . 
     U.S. Pat. No. 3,004,750 A discloses a stator for compressor or turbine arrangement which shows especially turbine arrangement which shows especially in  FIGS. 1 to 4  that in a stationary component which is the shroud  2  several through-holes  8  are provided through each of which a vane  6  can be inserted. Each vane  6  provides at its radially outer end a so called foot  10  overlying the outer surface of the outer shroud  2 , so that when the vane  6  is inserted into the slot  8 , the slot is sealed air tightly especially by welding  12  the foot  10  against the outer surface of the shroud  2 . The radially inner end of the vane  6  extends into a slot  26  in the inner shroud  4 . Inside the slot  26 , there is a spring pin  32 , which provides a damping effect on the vane  6 . 
     A similar construction of mounting of vanes  34  within a gas turbine engine is disclosed in U.S. Pat. No. 4,643,636 A, which shows an assembly including a ceramic inner and outer shroud rings in which recesses are provided through which vanes can radially mounted therein. For securing of the vanes a ceramic outer support ring  40  slides over the outer shroud ring 
     FR 2 671 140 A1 discloses guide vanes for a turbo machine compressor (see  FIG. 1 ). Inside the outer shroud segment  2 , through-holes  7  are provided through which vanes  3  can be inserted radially. The radially inner end of the vane is received by a slot of an inner ring segment  4 . The vane  3  can be secured by a fixing plate  9 , which is pressed inside a recess  10  at a mounting device  8  fixed on the outer shroud  2 . 
     SUMMARY 
     It is an object of the invention to provide a stationary gas turbine arrangement with at least one turbine stage comprising at least a first row of vanes being mounted at a stationary component arranged radially outside of the first row of vanes and extending radially into an annular entrance opening of the turbine stage facing a downstream end of a combustor, which shall enable to reduce significantly the dissembling and assembling work for performing maintenance work on the stationary gas turbine. Especially the lift off process of the uppercasing half of the turbine stage casing shall be avoided. 
     The object is achieved by the sum total of the features of claim  1 . Claim  6  is directed to a method for performing maintenance work on a stationary gas turbine. The invention can be modified advantageously by the features disclosed in the sub claims as well in the following description especially referring to preferred embodiments. 
     The inventive idea leaves the use of typical vanes consisting of an airfoil, an inner, and an outer platform made in one piece as depicted and explained in connection with  FIG. 2 . Especially by using a vane, which can be assembled by at least two separate parts, i.e. a separate airfoil and outer platform and a separate inner platform, preconditions are created to provide a direct access to the inner region of a first turbine stage without removing the uppercasing half of the turbine stage. It is also possible to use vanes of three separable parts, i.e. outer platform, airfoil, and inner platform. The inventive stationary gas turbine arrangement provides a radially orientated through-hole within the stationary component for each vane designed and arranged such that a radial insertion and removal of the airfoil of the vane is possible. Typically, the cross section of such a through-hole is in the shape of the largest airfoil profile so that the airfoil of the vane can be moved through the through-hole in its entire airfoil length. 
     In a preferred first embodiment, the airfoil of each vane has at its end directed radially inwards an extension for inserting into a recess of an inner platform for the purpose of a detachable fixation. As it will be described later, the inner platform is connected with an inner structure respectively inner component of the turbine stage. 
     The other end of the airfoil directed radially outwards provides a contour, which is adapted such the through hole can be closed airtight by using an additional detachable fixation means. Therefore, in an assembled state the airfoil of the vane is detachable fixed at both ends in contrast to the embodiment according to state of the art shown in  FIG. 2  in which the inner platform is spaced from the inner structures of the turbine stage respectively spaced from the inner combustor liner. 
     In another embodiment the outer end of the airfoil, which is named as other end directed radially outwards, can be non detachable connected, i.e. in one piece, with an outer platform having a platform shape which fits into the through-hole in the stationary component such that the outer platform closes the through-hole airtight by suitable fixation means. 
     In a further embodiment the airfoil of each vane has at its end directed radially inwards an inner platform or at least a little shape in the form of an inner platform which is spaced inwards to components of the turbine stage so that a cooling channel is limited through which a purge flow of cooling medium can be injected into the hot gas channel of the turbine stage. The outer end of the airfoil provides at least a contour which is adapted such the through hole can be closed airtight by using an additional detachable fixation means. 
     In all cases of embodiments according to the invention, it is possible to insert or remove the airfoil of the vane radially through the through-hole inside the stationary component. 
     In case of a fixed position, by at least the fixing means at the outer end of the airfoil, the airfoil of the vane stays in close contact or is connected in one piece with the inner platform which boarders the hot gas flow through the turbine stage towards the inner diameter of the hot gas flow channel of the turbine stage. On the other hand the outer platform which is connected with the airfoil in a flush manner or which is manufactured in one piece with the airfoil borders the hot gas flow channel radially outwards. All inner and outer platforms of the vanes of the first row being aligned adjacent to each other in circumferential direction limit an annual hot gas flow in the area of the entrance opening of the turbine stage. 
     In case of a detachable fixation between the inner end of the airfoil and the inner platform as mentioned before in connection with the first preferred embodiment the inner platform provides at least one recess for insertion the hook like extension of the airfoil at its radially inwards directed end so that the airfoil is fixed at least in axial and circumferential direction of the turbine stage. As it will be described later in reference to an illustrated embodiment the hook like extension has a cross like cross section, which is adapted to a groove inside the inner platform. The recess inside the inner platform provides at least one position for insertion or removal at which the recess provides an opening through which the hook like extension of the airfoil can be inserted completely only by radial movement. The shape of the extension of the airfoil and the recess in the inner platform is preferably adapted to each other like a spring nut connection. 
     For insertion or removal purpose it is possible to handle the airfoil only at its radially outwards directed end which is a remarkable feature for performing maintenance work at the turbine stage without the need of lift of the upper casing half of the turbine stage as will described later. 
     A further opportunity for repair work at the first turbine stage it is favorable that the inner platform is separately fixed to the inner structure. In a preferred embodiment the inner platform is detachably mounted to an intermediated piece, which is also detachably mounted to the inner structure respectively inner component of the turbine stage. Hereto the intermediate piece provides at least one recess for insertion a hook like extension of the inner platform for axially, radially and circumferentially fixation of the inner platform. Basically, the intermediate piece allows some movement of the inner platform in axial, circumferential, and radial direction. There are some axial, circumferential, and radial stops in the intermediate piece to prevent the inner platform from unrestrained movements. With the axial and circumferential stop the vane airfoil is not cantilevered but supported at the outer and inner platform. An additional spring type feature presses the inner platform against a radial stop within the intermediate piece, so that the airfoil can be mounted into the outer and inner platform by sliding the airfoil radially inwards from a space above the outer platform liner. 
     The connection techniques used for connecting the airfoil with the inner platform, the inner platform with the intermediate piece and the intermediate piece with the inner structure of the turbine stage are chose suitably such a worker can easily mount or dismantle each of the connections easily without the need of much mounting space. 
     Typically a turbine stage of a gas turbine arrangement is encapsulated by a casing in which at least one manhole is provided to get access for a worker to the inner section of the stationary components of the turbine stage. Inside the casing is enough space for a worker to mount or demount at least one vane by radially insertion and/or removal the airfoil through the through-hole of the stationary component. In case of removing a for example defective airfoil of a vane a worker has access to the fixation means which fixes the airfoil of the defective vane with the stationary component. After releasing the fixation means the worker has access to the radially outwards directed end of the airfoil so that the worker can handle the airfoil at its airfoil tip. Now it is possible to remove the airfoil at its extension radially out of the recess of the inner platform and to remove the airfoil completely out of the turbine stage through the through hole inside the stationary component. 
     Since all vanes of the first vane row are equipped with such fixation means inventively it is possible to remove one after the other all vanes out of the turbine stage. 
     For further maintenance work especially at the first row of blades it is possible to get a direct access by entering the space of the combustor through a further manhole, for example by removing the burner for getting access into the combustor through the burner opening. In a next step it is possible to remove the inner platform and following the intermediate piece to get a direct access to the first blade row. 
     Basically the inventive attachment of the vanes is not limited to vanes arranged in the first row of a gas turbine, so that all vanes of a gas turbine can be fixed at their outer end of the airfoil in a detachable manner for an easy inspection. More details are given in combination with the following illustrated embodiments. 
    
    
     
       BRIEF DESCRIPTION OF THE FIGURES 
       The invention shall subsequently be explained in more detail based on exemplary embodiments in conjunction with the drawings. In the drawings 
         FIG. 1  shows a rough sketch of a longitudinal section through a part of a first turbine stage with a combustor exit, 
         FIG. 2  shows a rough longitudinal section through the first turbine stage according to state of the art, 
         FIGS. 3 a , 3 b , 3 c , and 3 d    show an airfoil with extension and an inner platform, 
         FIGS. 4 a  and 4 b    show a cross sectional and top view of an intermediate piece, 
         FIGS. 5 a  and 5 b    are sectional views through the radially outward directed end of the airfoil with fixation means to the outer platform, 
         FIGS. 6 and 7  are sketches to illustrate performing maintenance work on a stationary gas turbine and 
         FIG. 8  is an alternative airfoil with an inner platform spaced apart from stationary turbine component. 
     
    
    
     DETAILED DESCRIPTION 
       FIG. 1  shows a rough schematically longitudinal section of a first turbine stage  6 , which is downstream arranged to a combustor  4 . The turbine stage  6  provides a first row of vanes  1 , which is followed in axial flow direction by a first row of blades  2 . To get a direct access to the stationary components  13  of the turbine stage  6  inside a casing  17  encapsulating at least parts of turbine stage  6  as well parts of the combustor  4  at least one manhole  18  is provided which is lockable air tightly. 
     Each vane  1  of the first row of vanes is assembled in parts, so that the airfoil  1 ′, the inner platform  10  and the outer platform  9  are separate parts. In case of the embodiment shown in  FIG. 1  it is assumed that the outer platform  9  of the vane is part of the stationary component  13  of the turbine stage. The outer platform  9  provides a through hole  19 , which is typically adapted to the largest cross section of the profile of the airfoil  1 ′ of the vane  1 . The radially outward directed end of the airfoil  1 ′ has a shape adapted to the shape of the through hole  19  so that the end of the airfoil tip closes the through hole  19  air tightly. 
     Further there are fixation means  20  (shown in  FIG. 5 ) which connects the radially outwards end of the airfoil  1 ′ with the stationary component  13  respectively with the outer platform  9 . The radially inwards directed end of the airfoil  1 ′ provides a hook like extension  21 , which is inserted into the inner platform  10 , which is connected to an intermediate piece  22  being detachably fixed with inner structures of the turbine stage  6 . 
     The airfoil  1 ′ of the vane  1  is connected radially with its outer and inner end. In addition by separating the outer platform from the airfoil  1 ′ it is possible to design the outer platform  9  integrally with the outer combustor liner  15 ′ to remove the leakage line  14 ′ as explained in  FIG. 2 . Of course, it is possible too to design the outer platform  9  and the outer combustor liner  15 ′ as separate parts, which can enclose a purge flow gap  14 ′ as in case of  FIG. 2 . 
     On the other side the mating faces of the inner platform  10  and the inner combustor liner  15  are inclined more to aerodynamically better introduce the purge flow into the main flow  3 . The new design allows further an overlap of the inner platform  10  and the inner combustor liner  15 . 
       FIG. 3 a    shows a side view of an airfoil  1 ′ of a vane having an end directed inwardly at which a hook like extension  21  is arranged protruding over the length of the airfoil  1 ′. The extension  21  has a cross like cross-section, which is illustrated in  FIG. 3 b   . The inner platform  10 , which is illustrated in  FIG. 3 c   , has a recess  21 ′ of cross like cross section for insertion the extension  21  only by radial movement. The depth of the recess  21 ′ is larger than the radial length of the extension  21 , so that radial movement of the extension  21  within the recess  21 ′ remains possible for example to compensate different thermal expansion effects between the turbine components. Due to the cross sectional shape of the extension  21  and the recess  21 ′, the airfoil is fixed axially and in circumferential direction. 
       FIG. 3 d    shows a side view of the inner platform  10 , which also provides at its bottom face two hooks  34  for mounting in the intermediate piece  22 . 
       FIGS. 4 a  and 4 b    show a cross sectional view as well a top view of recesses inside an intermediate piece  22 . In case of the illustrated embodiment the intermediate piece  22  provides two separate recesses  24  each of the recesses can receive the hooks  34  of one inner plate  10 . So it is possible to fix at least one inner plate  10  at one inter mediate piece  22 . Each of the recesses  24  shown in  FIG. 4 b    has openings  25  to receive a hook  34  of the inner platform  10 , which typical has a T-like cross section. Further the recess  24  provides an axial groove  26  having also a T-cross section  27  as illustrated in  FIG. 4 a    shows a section view along the section line A-A. By sliding the T-shaped hooks  34  axially along the recess  24  a position can be reached in which the inner platform  10  is fixed radially, axially and in circumferentially direction. 
       FIGS. 5 a  and 5 b    illustrate sectional views of two alternative embodiments of a fixation means  20  for the outer directed end of an airfoil  1 ′. The embodiment shown in  FIG. 5 a    illustrates the outer platform  9  having a through-hole  19  providing a contoured rim surface  28  at which the outer end of the airfoil  1 ′ aligns with its contour  23  air tightly. To fix and press the outer end of the airfoil  1 ′ against the through hole  19  a fixation means  20  is used which is a bar  29  fixed by screws  30  onto the outer platform  9  by pressing the airfoil  1 ′ directed radially inwards. 
     In  FIG. 5 b    another sealing and fixing mechanism is discloses. Here the upper end of the airfoil  1 ′ has a protruding collar  33  which is pressed by the bar  29  into a nut like recess  31  inside the outer platform  9  in which a chord seal  32  is inserted. In the same way as in  FIG. 5 a    the bar  29  is pressed and fixed against the upper end of the airfoils by screws  30 . 
     For performing maintenance work inside the first turbine stage  6  first it is necessary to get an access to the space between the casing  17  and the stationary components  13  of the stationary turbine  6 , see  FIG. 1 . A worker man has to open the man hole  18  above the first stage vane. In a second step the worker has to remove the fixation means  20  so that the airfoil  1 ′ can be radially drawn out of the gas turbine. In response to the extent of the maintenance work the worker can remove one vane or all vanes  1  in the before manner since all vanes are designed and fixed inside the first row of vanes in the same manner. 
       FIG. 6  illustrates the situation in which the vanes are removed completely out of the turbine stage  6 , which is shown by the open through-hole  19  inside the outer platform  9 . The worker man gains access into the space of the combustor  4  by a further manhole for example by demounting the burner arrangement from the combustor liner (not shown). Now the worker has access to the inner platform  10 , which can be removed by pressing down and moving in axial direction towards the combustor liner  15 . The inner platform  10  can then be tilted in upstream direction and removed downstream for final release. In a next step the intermediate piece  22  can also be removed completely out of the turbine stage  6  as illustrated in  FIG. 7 . Now the worker has a direct access to the first stage blade  2 . Finally the first stage blade  2  can also be removed, if required it is possible to replace labyrinth sealing  35 , which between the intermediate piece  22  and the stationary components of the turbine stage, before reassembling the first turbine stage by carrying out the explain steps in reverse order. 
       FIG. 8  shows an alternative fixation of a vane  1  which provides an airfoil  1 ′, an inner platform  10  and a small fragment of an outer platform  10  in one piece. The inner platform  10  is spaced apart from the inner combustor liner  15  and limits a gap  14  through which a purge flow of cooling medium can be injected into the hot gas flow  3 . The outer platform  9  fits airtight in a through-hole  19  inside the stationary component  13 . The outer end of the outer platform  9  is pressed radially inwards by a bar  29  which is fixed by at least two screws  30  at the stationary component  13 . The size and shape of the through-hole  19  has to be adapted to the largest diameter of the vane  1 , which may be in the section of the inner platform  10  to ensure that the whole vane  1  can be removed completely and easily by radial movement only. All reference signs in  FIG. 8  being not mentioned yet concern to components, which are explained in detail in connection with  FIG. 2 . 
     The inventive stationary gas turbine arrangement leads to couple of significant advantages as listed in the following: 
     a) Enabling 1 st  stage disassembly while casing and rotor are not lifted—only manholes must be opened. This is equivalent to a significant reduction in engine outage time. In turn this is a considerable commercial benefit for the gas turbine operating company. 
     b) Enabling of replacement of individual airfoils, individual inner diameter platforms and individual 1 st  stage blades. This is equivalent to a significant reduction in engine outage time. In turn, this is a considerable commercial benefit for the gas turbine operating company. 
     c) Due to integration of outer platform into the outer combustor liner cooling air leakage is reduced because gap between combustor liner and vane platform disappears being equivalent to a performance increase. 
     d) Enabling of reducing aerodynamic losses due to better alignment of purge and main flow from gap between combustor liner and vane platform into the main flow being equivalent to a performance increase. 
     e) Labyrinth seal can be replaced easily.