Abstract:
The invention pertains to a seal element for sealing a gap, in particular within a turbo-machinery, between a first component and a second components spaced apart from each other, said first component having a first surface and said second component having an opposing second surfaces. The seal element comprises a support structure and a sealing structure covering at least partially said support structure. The support structure comprises at least two contacting members, each contacting member serves for putting a portion of the sealing structure in contact with one of the surfaces and being capable of following a deformation of said surface. The invention further pertains to a combustion turbine, wherein a gap is formed between a first surface and a second surface, which gap is sealed off by said seal element.

Description:
BACKGROUND OF THE INVENTION  
     Field of the Invention  
       [0001]     The invention relates to a seal element for sealing a gap which may be formed between spaced-apart first and second components, in particular of a turbo machinery like a combustion turbine. The invention also relates to a combustion turbine having a seal element.  
         [0002]     In industrial plants, particularly thermo-mechanical machines and chemical plants, in which different fluids are used, it may be necessary to keep those fluids separate from one another within the plants. For example, in thermal combustion power plants, flow regions of hot combustion gases have to be separated sealingly from flow regions of cooling gases of lower temperature. In gas turbine plants with high turbine inlet temperatures, for example of more than 1000° C., thermal expansions of the individual components of the gas turbine plant occur, so that adjacent components are sometimes spaced from one another through the use of a gap in order to avoid high thermal stresses and the formation of cracks. Such gaps may constitute connections between flow regions of hot gases and flow regions of cold gases. It is advantageous to seal off the gap to reduce the inflow of cold gas into the flow region of hot gases so as not to thereby lower the temperature in the flow region of hot gases.  
         [0003]     U.S. Pat. No. 3,341,172 and U.S. Pat. No. 2,991,045, each of which describes a gas turbine with an outer casing and a two-part inner casing, accordingly specify a sealing element that has a cross-section in the shape of an elongate C for sealing a gap between the two inner casings. An annular gap, through which cooling fluid is guided, is formed between the inner casing and the outer casing. The hot gas for driving the gas turbine flows within the inner casing.  
         [0004]     U.S. Pat. No. 4,537,024 describes a gas turbine plant, in which components of a nozzle structure are sealed through the use of axial and radial sealing elements. The sealing elements are intended to prevent hot gas which flows through the nozzle structure from infiltrating into turbine regions outside the hot-gas duct. A sealing element can have approximately the shape of a squashed eight as seen in cross-section.  
         [0005]     U.S. Pat. No. 5,975,844 describes in an assembly including two mutually thermally movable components each having a component groove located one opposite the other, a sealing element. This sealing element is directed along a main line for sealing a gap between the components. It comprises a first end, a second end opposite the first end and a middle region, in a cross-section substantially perpendicular to the main line, along a centre line, whereby the middle region is disposed between the ends and the sealing element having a toothed first surface.  
         [0006]     U.S. Pat. No. 5,657,998 relates to a gas-path leakage seal for generally sealing a gas-path leakage-gap between spaced-apart first and second members of a gas turbine, in particular first and second segments of a gas turbine combustor casing. This seal comprises a generally imperforate foil-layer assemblage consisting essentially of materials selected from the group consisting of metals, ceramics, and polymers. This foil-layer is impervious to gas and it is disposed in the gas-part leakage-gap. The foil-layer assemblage having a first foil-layer with a lengthwise direction. The gas leakage seal further comprises a cloth-layer assemblage covering and contacting generally the entire first foil-assemblage outer surface and consisting essential of materials selected from the group consisting of metals, ceramics and polymers. Preferably the cloth-layer assemblage has two layers each have a thickness of about 10-25 microns. The cloth-layers each are woven cloth-layers and each comprises a high temperature, nickel-based super-alloy, such as Inconel X-750. The seal assemblage is either fixed in grooves of adjacent parts of a gas turbine, or introduced in a U-shape flange of a combustor, or used in a twin-seal installation or in a multi-seal installation. In either case the seal fully lies within the leakage-gap, and provides a sealing effect either by contacting a surface within the gap, being inserted in a groove or contacts another seal assemblage. In comparison to a conventional metal rigid seal this seal with two foil-assemblages reduces the gas-path leakage from 2.4% to generally 1.0% according to U.S. Pat. No. 5,657,998.  
       SUMMARY OF THE INVENTION  
       [0007]     It is an object of the invention to provide a seal element for sealing a gap, in particular a gas-path leakage gap of a turbo machinery like a combustion turbine. It is a further object of the invention to provide a combustion turbine with a seal element.  
         [0008]     With the forgoing and other objects in view there is provided in accordance with the invention, a seal element for sealing a gap between a first component having a first surface and a second component having a second surface and being spaced apart from the first component. The seal element comprises a support structure and a sealing structure covering at least partially the support structure. The support structure comprises at least two contacting members, whereby each contacting member serves for putting a portion of the sealing structure in contact with one of the surfaces and being capable of following a deformation and/or movement of said surface.  
         [0009]     The invention takes into consideration the perception that in an apparatus having parts being exposed to different temperatures different thermal expansions and deformations occur. For example in furnaces or more general hot gas chambers, as in a gas turbine, those parts being exposed to a hot gas during the stationary operation conditions of the apparatus are exposed to higher temperatures than those parts, in particular wall components, not directly exposed to the hot gas. The resulting different thermal expansions of the parts are compensated by gaps left between parts for freely expanding. In combustion turbines for example it is often necessary to hinder the hot gas to flow through the gap, as parts behind the gap may not be capable to withstand the high temperature of the hot gas. Therefore cooling fluid under a higher pressure than the hot gas is fed to the gap. A portion of this cooling gas than flows as leakage-gas through the gap into a stream of the hot gas thereby hindering the hot gas to flow into the gap. In a gas turbine this high pressure cooling gas is taken from the compressor of the gas turbine and due to the leakage through the gap can not be used for the combustion process which reduces the efficiency of the gas turbine. To reduce the amount of leakage gas seal elements are provided for sealing the gap. Design and manufacture of suitable seal elements becomes the more difficult the more curved the shape of the gap is, the higher a lateral movement of the gap is and the higher the temperature of those surface which are in contact with the seal element become. A even more complicated situation arises when those surface become permanently uneven, in particular due to relaxation processes or inelastic deformations.  
         [0010]     With the seal element according to the invention the contacting members cope with those deformations and movements of the first and second components, while the sealing structure still contacts the surface and so preventing cooling fluid from flowing between sealing structure and surfaces. By choosing suitable materials for the support structure and the sealing structure respectively the seal element can be used for temperatures of over 500° C. and up to over 1300° C. Unlike other seals as one-piece metallic seals or metallic brush seals, which are capable to cover only a certain movement of the gap or are quite expensive, need a rather large space and can only be used for slightly curved surfaces the seal element according to the invention is simple to manufacture, cost efficient, capable to cope with curved surfaces as well as steps in the surfaces and is able to follow movements and deformations of the gap or the surfaces.  
         [0011]     According to the invention the sealing function performed by the sealing structure is separated from the ability of elastic deformation performed by the support structure. By use of at least two contacting members the seal element is less stiff then a one-piece metallic seal wherein the metallic structure also fulfils the sealing function. As preferably each contacting member has the ability for deformation and movement independently from the others a sealing of large deformed or uneven surfaces is possible. This also includes surfaces having steps, which can occur in attached segments of a gas turbine, like blades, vanes, heat shield elements of a combustion chamber.  
         [0012]     In accordance with another feature of the seal element the sealing structure comprises a web having metallic and/or ceramic fibres. By virtue of the web of ceramic or metallic fibres which form a flexible and deformable sealing portion a good sealing performance can be assured. Ceramic fibres as well as certain metallic fibres can be used up to temperatures of about 1200° C. or even more. The seal element is therefore useable for sealing components of a turbo machinery, furnaces, burners or the like, which are exposed to hot gases. Depending on the mesh-size of the web the sleeving and therefore the seal-element is gas pervious, so to some extend the cooling gas may flow through the sleeving thereby cooling the fibres. This leads to an effusion cooling of the seal element Also regions and turbine parts in the vicinity of the gap outside of the cooling gas region can be cooled by the cooling gas penetrating the sealing structure.  
         [0013]     In accordance with a further feature the sealing structure comprises a ceramic fibre fabric, a ceramic fibre tape, a ceramic fibre sleeving or a ceramic fibre mat. Preferably the ceramic fibres essentially consisting of a material like Zirconia (ZrO 2 ), Silica (SiO 2 ) or Alumina (Al 2 O 3 ). It is understood that those ceramic materials could be combined and also be stabilised by other materials like Yttria (Y 2 O 3 ). For example the ceramic fibres may essentially consist (in weight %) of 62.5% Al 2 O 3 , 24.5% SiO 2 , 13% B 2 O 3  with a crystal phase of Mullite-type and amorphous or solely amorphous; of 70% Al 2 O 3 , 28% SiO 2 , 2% B 2 O 3  with γ-Al 2 O 3 , Mullite and amorphous SiO 2 ; of 73% Al 2 O 3 , 27% SiO 2  with γ-Al 2 O 3  and amorphous SiO 2 , of 89% Al 2 O 3 , 10% ZrO 2 , 1% Y 2 O 3  with α-Al 2 O 3  and Yttria stabilised Zirconia; of 85% Al 2 O 3  and 15% SiO 2  with α-A 2 O 3  and Mullite; of &gt;99% Al 2 O 3  as α-Al 2 O 3 . Such ceramic fibre materials are for example available from 3M (Minnesota Mining and Manufacturing Company), St. Paul, Minn., USA under the Trademark of “Nextel”. The manufacturing of ceramic fibres as well as the manufacturing of a web comprising ceramic fibres are know to those skilled in the art. Therefore a suitable web comprising ceramic fibres fulfilling specified properties, in particular heat resistance up to over 1200° C. to about 1372° C., flexibility and other mechanical features may be chosen by those skilled in the art to provide a sealing structure bounded to or just covering the support structure. Other features like porosity and decree of gas perviousity can be provided in a predefined range.  
         [0014]     In accordance with an added feature the sealing structure comprises a metallic fibre fibric, a metallic fibre tape, a metallic fibre sleeving or a metallic fibre mat. As metallic fibres are quite ductile and not brittle they are as well elastically as plastically deformable and form a web which resists high thermal and mechanical loads. Preferably the metallic fibres consist of a superalloy, in particular a nickel-based, a cobalt-based or iron-based superalloy  
         [0015]     In accordance with an additional feature the sealing structure is loosely connected to the support structure. The sealing structure preferably itself is an object manufactured separately from the support structure. It is put in contact with the support structure for covering at least a portion of the support structure after its own manufacturing. So it preferably provides a loose contact with the support structure and is removable from the support structure. In the latter case it could easily be replaced during maintenance of a turbo machinery by a new web. In an embodiment in which the sealing structure is provided as a sleeving the support structure is introduced into the sleeving and so all surfaces of the support structure are surrounded by the web of fibres. It is also possible to provide a ceramic fibre sealing structure, for example a layer, tightly bounded to the support structure.  
         [0016]     In accordance with yet another feature the support structure consists of a metal, in particular a sheet metal. Having a support structure of a metal allows a simple manufacturing of the contacting members, for example by simply cutting slits into the metal. Suitable metals are those who withstand high temperatures, for example high temperature steels like chromium steels or high temperature alloys on the basis of nickel or cobalt. The metal piece may extend along a centre line, whereby slits and/or recesses parallel and or perpendicular to the centre line lead to independently deformable contacting members, in particular vat-like contacting members. Such a piece of metal may also be bent or curved along the centre line and around the centre line, so that either a cylindrical shape or ring shape can be easily achieved. Having a support structure with slits and/or recesses reduces the stiffness. So compared to a more stiff structure larger deformations can be carried out under the same internal stress applied  
         [0017]     In accordance with yet a further feature the support structure has a curved form, in particular is U-shaped, open-ring shaped or ring-shaped. A curved support structure can be pre-stressed when put into contact with the surfaces, so that deformations of the surfaces which compress the support structure or give the support structure the opportunity to expand will coped by the contacting members without losing contact with the surfaces.  
         [0018]     In accordance with yet an added feature the support structure has a frame portion to which said contacting members are connected via a branch portion extending away from said frame portion The contacting members may have a vat-like form. Having a branch portion to which the contacting member is connected assures for the contacting member the ability to deform and move in a three-dimensional way. The branch portion and the contacting member may in addition be twisted and bent.  
         [0019]     The branch portions may form together with a middle portion a two-arm spring. In such a spring each branch portion forms one arm of the spring, whereby in the middle portion the spring may be bent to form one or more loops. With the middle portion the spring may be connected to the frame portion, which frame portion may have a suitable opening, hook or the like. The spring may be made of any suitable wire, preferably metallic wire, whereby the contacting members may be formed a bend wire portions. Preferably the branch portion and the contacting member are elastically deferrable.  
         [0020]     In accordance with yet an additional feature the support structure has at least two branch portion with different length. Having branch portions with different length is in particular useful when surfaces with steps, grooves, recesses or ridges have to be sealed.  
         [0021]     In accordance with a concomitant feature the seal element comprises a tightening member for tightening said sealing structure between two adjacent contacting members. Preferably the tightening member comprises a spring member, in particular a spring ring. Applying a tightening member for tightening the sealing structure insures that the sealing structure is in close contact with the surfaces so that during different operating conditions, different temperatures and during a long period of time the seal element assures a good sealing effect. In particular in a seal element with a support structure surrounded by a sleeking, this sleeking may form a pleat which will be smoothened by a tension created by the tightening member. The tightening member may be permanently connected to the seal element, in particular to the sealing structure or it may be removable connected to the seal element. So the seal element may comprise two or three distinct parts (sealing structure, support structure, tightening member) which fulfil different tasks and which can be separated from each other, in particular replaced by other compatible parts in case of repair, maintenance or renewal.  
         [0022]     In accordance with again another feature the seal element is placed in a hot gas chamber for sealing a gap. The hot gas chamber has a hot-gas flow region surrounded by a wall structure, which comprises the second component with the second surface. A first component being attached to the wall structure and having the first surface, which is directed to the wall structure. The gap is formed between the first component and the second component, in particular between the first surface and the second surface. The sealing structure is in contact with the second surface of the second component and with the first surface of the first component thereby sealing the gap. Preferably the hot gas chamber is a part of a combustion turbine, in particular is a combustion chamber or a turbine section. The combustion chamber may be one of a jet engine, a turbine of an automotive or a submarine or the like. It may also be the combustion chamber of a stationary gas turbine in particular one for producing electrical power. The combustion chamber may be a ring chamber or a can-like chamber, whereby in a gas turbine two or more can-like combustion chambers may be used. In a combustion turbine having a number of burners, with each burner connected to a turbine section by a separate duct or can, a seal element as described above may serve to seal a turbine inlet for hot gas to enter the turbine section and a respective duct (can) ending in the vicinity of the turbine inlet for allowing hot gas to flow from the burner to the turbine inlet.  
         [0023]     In accordance with again a further feature the seal element seals a gap, wherein the first component is a heat shield element of a combustion chamber or a shroud element of a turbine section. In a ring combustion chamber a metallic heat shield may be multiply curved, so that the seal element with contacting members following the shape and the deformation of the surfaces of the heat shield is most efficient. In a can-like combustion chamber the seal element is preferably used to seal the region between can and entrance into the turbine section. It may also be used for sealing a gap between metallic heat shield elements with a closed loop cooling fluid circuit and a wall structure.  
         [0024]     The seal element may also be used to seal off a gap between components which are not spaced apart in radial direction of a gas turbine but disposed in axial and circumferential direction, wherein at least first and second of the components are spaced apart in the circumferential direction or in the axial direction by a leakage-gap. Those components have an inner surfaces exposed to the hot gas region and an outer surfaces exposed to the cooling gas region. The seal element can be used to seal either a gap between first and second components in the axial direction or between first and second components in the circumferential direction.  
         [0025]     In accordance with another object of the invention it is provided a combustion turbine having a gas-leakage gap which is seal by a seal element. The combustion turbine comprises a hot gas chamber having a hot-gas flow region, a wall structure surrounding the hot-gas flow region and comprising at least one second component having a second surface directed to the hot-gas flow region. At least one first component is attached to the wall structure and has a first surface, which is directed to the wall structure. The gap is formed between the first component and the second component, in particular between the first surface and the second surface. The seal element for sealing the gap comprises a support structure and a sealing structure covering at least partially the support structure. The support structure comprises at least two contacting members, each of which puts a portion of the sealing structure in contact with one of the surfaces and being capable of following a deformation of the respective surface. The sealing structure further being in contact with said second surface of the second component and with the first surface of the first component thereby sealing the gap.  
         [0026]     In accordance with yet another object of the invention it is provided a combustion turbine having a gap between a duct and a turbine inlet, which gap is seal by a seal element. The turbine inlet is an opening which allows hot gas to enter a turbine section of the combustion turbine. The duct connects a combustion chamber of a burner, in which the hot gas is generated to the turbine inlet.  
         [0027]     All of the advantages and features of the seal element described in more detail above also hold for the combustion turbine having this seal element, in particular the features and advantages with respect to the seal element comprising a curved frame portion from which the contacting members are spaced apart and whereby each contacting member being connected to the frame portion via a branch portion. Preferably the seal element is surrounded by the sealing structure being a sleeving.  
         [0028]     Although the invention is illustrated and described herein as embodied in a seal element for sealing a gap and a combustion turbine, it is nevertheless not intended to be limited to the details shown, since various modifications and structural changes may be made therein without departing from the spirit of the invention and within the scope and range of equivalents of the claims.  
         [0029]     The construction of the seal element and the turbine of the invention, however, together with additional objects and advantages thereof will be best understood from the following description of specific embodiments when read in connection with the accompanying drawings. 
     
    
     BRIEF DESCRIPTION OF THE DRAWINGS  
       [0030]      FIG. 1  is a fragmentary, diagrammatic, longitudinal-sectional view of a combustion turbine;  
         [0031]      FIG. 2  is an enlarged, fragmentary, cross-sectional view of a seal element in a combustion turbine;  
         [0032]      FIG. 3  is a fragmentary plan view of a sealing structure of a seal element;  
         [0033]      FIG. 4 . is a cross-sectional view of a seal element along line III-III of  FIG. 3 ;  
         [0034]      FIG. 5  is fragmentary winding off view of a sealing structure along line II-II of  FIG. 3 ;  
         [0035]      FIG. 6  is a perspective view of a ring shaped seal element.  
         [0036]      FIG. 7  is a fragmentary, diagrammatic, longitudinal-sectional view of a combustion turbine;  
         [0037]      FIG. 8  is a perspective view of the burner section of the combustion turbine of  FIG. 7 ;  
         [0038]      FIG. 9  is a perspective view of a support structure of a seal element;  
         [0039]      FIG. 10  is a winding off view of the support structure of  FIG. 9 . 
     
    
     DESCRIPTION OF THE PREFERRED EMBODIMENTS  
       [0040]     Referring now to the figures of the drawings in detail and first, particularly, to  FIG. 1  thereof, there is shown a in a cross-sectional view an upper portion of a combustion turbine (in the following also called gas turbine)  22  directed along a main axis  14 . The gas turbine  22  has along said main axis  14  a compressor (not further specified), a combustion chamber  19  and a turbine section  17 . Both combustion chamber  19  and turbine section  17  form a hot gas chamber  23  through which hot gas  24  generated in the combustion chamber  19  by burning air and fuel flows. In the turbine section  17  guide blades  16  and moving blades  15  are arranged in an alternating order along the main axis  14 . The guide blades or vanes  16  are directed perpendicular to the main axis  14  and are disposed along the circumference of the gas turbine  22  so as to form a circle.  
         [0041]     The gas turbine  22  comprises a respective wall structure  13  surrounding the combustion chamber  19  and the turbine section  17 . The respective wall structure  13  comprises second components  3  which—with respect to the combustion chamber  19 —are shown in more detail in  FIG. 2 . Surrounded by and attached to the wall structure  13  first components  2  are exposed to the flow of the hot gas  24 . A cooling gas region  28  is formed between the first components  2 , for example a guide-blade plate  12  or a heat shield element of the combustion chamber  19  and the components  3  of the turbine wall structure  13 . Cooling gas  25  is fed through cooling gas supply lines  30  in the respective cooling gas region  28 .  
         [0042]     The guide blades  16  are each connected to the wall structure  13  in the turbine section  17  through a guide blade plate  12 , which represents a first component  2 . A guide blade plate  12  is also referred to as shroud or the sealing strip on turbine blades. Its purpose is to supply rigidity to the blades, lessen vibration and provide to some extend a sealing between stages.  
         [0043]     Adjacent guide blades  16  are spaced apart from one another along the circumference so that they can essentially freely expand thermally. The guide-blade plate  12  separates the hot-gas region  11  formed around the main axis  14  of the gas turbine  22  from a cooling gas region  28  formed between the guide-blade plate  12  and the components  3  of the turbine wall structure  13 . The moving blades  15  extend radially outward perpendicular to the main axis  14 . The moving blades  15  lie completely within the hot-gas region  11 . This hot-gas region  11  is separated from the cooling-air region  28  by a plurality of first components  2 , also called as components of a seal ring, along the circumference of the gas turbine  22 . The components  2  are each adjacent to the moving blades  15 . For the sake of clarity, only one guide blade  16 , one moving blade  15  and one component  2  of the seal ring is shown for each turbine stage. A respective component  2  and guide-blade plate  12  is spaced apart from a respective component  3  of the wall structure  13  in the radial direction (direction perpendicular to the main axis  14 ) through a gas-leakage gap  5  (see  FIG. 2 ).  
         [0044]     This gap  5  is sealed off by a seal element  1 , thereby largely preventing a flow of cooling gas  25  out of the cooling-gas region  28  into the hot-gas region  11  and preventing hot gas  24  from flowing through the gap  5  in the cooling gas region  28 .  
         [0045]      FIG. 2  shows an enlarged cross-sectional view of a portion of a combustion chamber  19  like the one shown in  FIG. 1 . A seal element  1  is positioned between a first component  2 , which is a heat shield element of the combustion chamber  19 , and a second component  3 , which is part of a wall structure  13  surrounding the combustion chamber  19 . The heat shield element  2  has a side wall  29  directed towards a second surface  10  (also called an outer surface  10 ) of the wall structure  13 . Between the side wall  29  and the wall structure  13  a gas-leakage gap  5  having a width D remains. The heat shield element  2  has a first surface  9  (also called an inner surface  9 ) directed to the wall structure  13  and a hot gas surface  27 , which is opposite to the inner surface  9  and is exposed to a flow of hot exhaust gas  24 . The inner surface  9  as well as outer surface  10  of the wall structure  13  may be curved, may change their shape (deform) while being exposed to a high temperature or may have steps or the like. Between the heat shield element  2  and the wall component  3 , in particular between the inner surface  9  and the outer surface  10  a seal element 1 is positioned. In a cross-sectional view ( see  FIG. 4 ) the seal element  1  has an arc-like shape with contacting members  8  at the end of each side of the arc expanding almost perpendicular away from the ends of the arc. In a longitudinal direction the seal element 1 is curved along a centre line  26 , which almost describes a circle. The seal element  1  is completely surrounded by a sealing structure  6  in form of a sleeving web made of fibres. Those fibres consist either of ceramic materials or of a heat resistant metal. So to some extend, depending on the mesh-size of the web the sleeving  6  the seal-element 1 is gas pervious. The sleeving  6  is tightened by a tightening member  20  so that its surface is in close contact with the outer surface  10  and the inner surface  9  for sealing the gap  5 .  
         [0046]     The sealing structure  4  is generally gas impervious and has a frame portion  7 , which is slightly curved in a cross-section and ring-like curved along the centre line  26 . It consists of a metal strip formed from a sheet metal. The metal chosen for the support structure  4  is preferably a heat resisting steel or a high temperature NiCr alloy. The width of the support structure  4  is greater than the width D of the gap  5 . The support structure  4  gives the seal element  1  a good mechanical stiffness and elasticity, so that it also withstands high-pressure loads and the risk of breaking into parts and falling through the gap is avoided. The support structure  4  is covered on all sides by the sleeving  6 , in particular of ceramic fibres. The sleeving  6  of fibres defines a flexible and deformable sealing surface. The fibres consist preferably of a mixture of silica SiO 2  and alumina Al 2 O 3 , for example (in weight %) of 73% Al 2 O 3  and 27% SiO 2  with γ-Al 2 O 3  and amorphous SiO 2 .  
         [0047]     Between component  2  and component  3  a cooling gas region  28  is defined to which cooling gas  25  is supplied. The pressure of the cooling gas  25  is higher than the pressure of the hot gas  24 , which flows through the turbine  22  in the hot gas flow region  11 . Therefore a pressure difference exists which causes the seal element  1  to some extend to be pressed by the cooling gas  25  on the side wall  29  close to the gas-leakage gap  5 . As the sealing structure  6  is to some extend gas pervious the cooling gas  25  flows through the sleeving  6  thereby cooling the fibres. This leads to an effusion cooling of the seal element  1 . So also regions and turbine parts in the vicinity of the gap  5  outside of the cooling gas region  28  can be cooled. As the seal element  1  is capable to cope with deformations of the inner surface  9  and the outer surface  10  as well as radial and axial movements of the surfaces  9 , 10  an effective sealing of the gas-leakage gap  5  is assured and the amount of cooling fluid  25  needed is reduced. The cooling gas  25  saved in this way is now available for the combustion process.  
         [0048]      FIG. 3  shows a plan view of a portion of the support structure  4  of the seal element  1  according to  FIG. 2  along the centre line  26 . The support structure  4  has a frame portion  7 , whereby on both sides of the centre line  26  contacting members  8  are connected to the frame portion  7  through a respective branch portion  21 . So the contacting members  8  are connected to the frame portion  7  like vats. The support structure  4  with all its portions, frame portion  7 , contacting members  8  and branch portion  21  can be manufacture from one single metal sheet. The support structure  4  with a number of vat-like contacting members  8 , which together with the branch portions  21  are elastically deformable to follow movements or deformations of the first and second components  2 , 3 , allow an efficient sealing of the gap  5 .  
         [0049]     In  FIG. 4 a  cross-sectional view of a seal element  1  along line III-III of  FIG. 3  is shown. In this cross-sectional view the seal element  1  has a support structure  4  with a U-like shape, whereby the frame portion  7  forms the bottom of the U and the branch portions  21  form the sides of the U. At the end of each branch portion  21  a contacting member  8  extends perpendicular outwardly away from the branch portion  21 . The support structure  4  is completely surrounded by the sealing structure  6 . The sealing structure  6  is tightened by a tightening member  20 , which pushes the web of the sealing structure  4  into the U-shaped support structure  4 . So the web of the sealing structure  4  is tightened between two adjacent contacting members  8  along the centre line  26  and on the outer side of the support structure  4  between frame portion  7  and contacting members  8 .  
         [0050]     In  FIG. 5 a  fragmentary winding off view of the sealing structure  4  along line III-III of  FIG. 3  is shown. The vat-like contacting member  8  is connected to the frame portion  7  by the branch portion  21 . The branch portion  21  extends along a branch centre line  31 , to which it is symmetric. Both contacting member  8  and branch portion  21  are made of an elastically deformable material, in particular a metal. As the contacting member  8  is connected to the branch portion  21  only in the vicinity of the branch centre line  31  it has two arms, which can deform independently from the branch portion  21 . Furthermore the branch portion  21  itself can deform, in particular in a direction perpendicular to the connecting member  8 . So the sealing structure  4  can compensate any movement or deformation of the surfaces  9 ,  10  with the contacting members  8  remaining in contact with the surfaces  9 , 10 .  
         [0051]      FIG. 6  shows a perspective view of a ring shaped seal element  1  with a sealing structure  4  having a frame portion  7 , branch portions  21  and contacting members  8 . The sealing structure  4  is introduced in a sleeving  6  made of heat resisting fibre web. A spring ring  20  is provided in the inner circle of the ring like seal element  1  pushing the sleeving  6  into the support structure  4  for tightening the sleeving  6 .  
         [0052]      FIG. 7  is a cross-sectional view of a portion of a gas turbine  22  having a number of separate burners  41 , examples of this kind of turbine are described in U.S. Pat. No. 5,566,42 and U.S. Pat. No. 5,623,819. As can be seen, the gas turbine  22  has a compressor  40  for producing compressed air. The compressed air discharged from the compressor  40  is directed into the burner  41 , which is situated in a basket  42  (also called combustors) (only one of which is shown in  FIG. 7 ). The compressed air is heated by the combustion of fuel to generate a hot gas  24 . From the combustors  42 , the hot gas  24  is directed by ducts  43 (also called cans) to a turbine section  17 . Within the turbine section  17  the hot gas  24  flows over alternating rows of stationary vanes  16  and rotating blades  15 . The turbine section  17  has a number of turbine inlets  44 , each of which is assigned to one respective duct  43 . The duct  43  ends in the vicinity of the turbine inlet  44  (see  FIG. 8  which provides a perspective view of this). The arrangement of duct  43  and turbine inlet  44  is sealed of by a seal element  1 , which has the shape of a loop, in particular a almost rectangular loop following the shape of the turbine inlet.  FIG. 9  shows a perspective partial view of a support structure  4  of a seal element  1 . The support structure  4  has a frame portion  7 , in particular a metal strip or the like. The frame portion  7  has a fastening hook  35  forming an opening through which a two-arm spring  34  is fastened to the frame portion  7 . The two-arm spring  34  is made of a suitable metallic wire and has a middle portion  36 , which forms a loop wound through the fastening hook  35 . The middle portion  36  connects two arms of the spring  34 , which form elastically deferrable branch portions  21  of the seal element  1 . At the outer end of each branch portions  21  the spring  36  is bent to form contacting members  8  extending perpendicular to the branch portions  21 .  FIG. 10  shows a winding off view of the spring  34  of the support structure  4 , with the contacting members  8  forming an almost oval portion with a long straight, which long straight serves for contacting the sealing structure  6  to a respective of the surfaces  9 , 10  (see for example  FIG. 2 ).