WO2011047693A1 - Nozzle guide vane arrangement and turbine engine - Google Patents

Nozzle guide vane arrangement and turbine engine Download PDF

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Publication number
WO2011047693A1
WO2011047693A1 PCT/EP2009/007479 EP2009007479W WO2011047693A1 WO 2011047693 A1 WO2011047693 A1 WO 2011047693A1 EP 2009007479 W EP2009007479 W EP 2009007479W WO 2011047693 A1 WO2011047693 A1 WO 2011047693A1
Authority
WO
WIPO (PCT)
Prior art keywords
guide vane
nozzle guide
adjoining
ring segments
sealing element
Prior art date
Application number
PCT/EP2009/007479
Other languages
French (fr)
Inventor
Andrew Shepherd
Original Assignee
Siemens Aktiengesellschaft
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Priority to PCT/EP2009/007479 priority Critical patent/WO2011047693A1/en
Publication of WO2011047693A1 publication Critical patent/WO2011047693A1/en

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/501—Elasticity

Definitions

  • Nozzle guide vane arrangements in the hot section of a gas turbine are typically arranged in segments.
  • Each nozzle guide vane segment includes one or more vanes or aerofoils, respectively.
  • the pressure of the cooling air outboard of the outer platform or outer ring of the nozzle guide vane arrangement and inboard of the inner platform or inner ring of the nozzle guide vane arrangement is often higher than the main flow path pressure inside the nozzle guide vane arrangement. This means that the cooling air will leak into the main flow path at the split lines, i.e. gaps, between the nozzle guide vane segments. This leakage must be sealed to prevent performance losses . ,
  • the sealing elements are pressed in place by the cooling air due to the pressure difference of the cooling air pressure and the pressure of a fluid in the main flow path of the nozzle guide vane elements. That means each sealing element is pressed against the non-flowpath side of the nozzle guide vane elements, by which the gap is absolutely sealed.
  • the sealing element may be flexible.
  • Flexible in respect of the present invention may be defined as elastic, bendable, deformable, or adaptive, particularly in a radial direction perpendicular to the gap. This may be provided by a sheet of metal.
  • the pins are arranged ra- dially through the sides of the sealing element and through the sides of the end walls of the ring segments.
  • Both the lateral areas of the free ends of the ring segments of the nozzle guide vane segments and the sealing elements have each at least one hole for guiding at least one pin.
  • Advanta- geously the lateral area of the free ends and as well the sealing elements have two or more holes for receiving two or more pins. The pins are to hold the sealing elements in place when the engine is not operating. During operation the sealing elements are pressed in place by the cooling air pres- sure.
  • the surfaces may be considered substantially flat and no special treatment of the free ends 5 is necessary. They may be cylindrical as the remaining parts of the outer ring segment 3, without leading to nega- tive side effects.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

The invention relates to a nozzle guide vane arrangement, in particular of a turbine engine, comprising a plurality of nozzle guide vane segments (1), whereby a nozzle guide vane segment (1) comprises one or more nozzle guide vane(s) (2) and at a first side of the one or more nozzle guide vane(s) (2) an outer ring segment (3) and/or at the second side of the one or more nozzle guide vane(s) (2) an inner ring segment (4), whereby adjoining outer ring segments (3) and/or adjoining inner ring segments (4) are sealed by sealing elements (10), whereby a thin and flexible sealing element (10) is arranged at the outer lateral area of two adjoining outer ring segments (3), whereby the outer lateral area is that side of an outer ring segment (3) which is averted to the one or more nozzle guide vane(s) (2), and/or a thin and flexible sealing element (10) is arranged at the inner lateral area of two adjoining inner ring segments (4), whereby the inner lateral area is that side of an inner ring segment (4) which is averted to the one or more nozzle guide vane(s) (2), whereby each sealing element (10) covers the gap (6) between two adjoining outer (3) and/or inner ring segments (4). The invention relates further to turbine engine, in particular gas turbine engine, comprising one or more such nozzle guide vane arrangement (s).

Description

Description
Nozzle guide vane arrangement and turbine engine
The present invention relates to a nozzle guide vane arrange¬ ment, in particular of a turbine engine, comprising a plural¬ ity of nozzle guide vane segments, whereby a nozzle guide vane segment comprises one or more nozzle guide vane(s) and at a first side of the one or more nozzle guide vane(s) an outer ring segment and/or at the second side of the one or more nozzle guide vane(s) an inner ring segment, whereby ad¬ joining outer ring segments and/or adjoining inner ring segments are sealed by sealing elements. The invention relates further to a turbine engine, in particular a gas turbine engine, comprising one or more nozzle guide vane arrangement (s) .
Nozzle guide vane arrangements in the hot section of a gas turbine are typically arranged in segments. Each nozzle guide vane segment includes one or more vanes or aerofoils, respectively. The pressure of the cooling air outboard of the outer platform or outer ring of the nozzle guide vane arrangement and inboard of the inner platform or inner ring of the nozzle guide vane arrangement is often higher than the main flow path pressure inside the nozzle guide vane arrangement. This means that the cooling air will leak into the main flow path at the split lines, i.e. gaps, between the nozzle guide vane segments. This leakage must be sealed to prevent performance losses . ,
It is known that the sealing is achieved by assembling a small seal strip between the end walls of adjoining nozzle guide vane segments, fitting into narrow slots that are cut into the end walls of the outer and/or inner ring segments of a nozzle guide vane segment. The machining of the slots in the end walls of the outer and/or inner ring segment is generally done by EDM (EDM = electrical discharge machining) . This is a slow and expensive process. Another disadvantage of the EDM manufactured slots at the end walls of the outer and/or inner ring segments of the nozzle guide vane segment is that the slots are very difficult to inspect. Further, the surface finish of an EDM slot is quite rough. If the EDM slots are manufactured out of position, the strip seals can force the nozzle guide vane segments out of position, opening a leak path. The end walls of the outer and/or inner ring segment of a nozzle guide vane segment have to be cast thicker than needed to accommodate the EDM slots. This is bad for flow path cooling and adds unwanted mass to the nozzle guide vane segments. Another disadvantage is that the EDM manufactured seal slots have to stop short at the forward and aft ends of each nozzle guide vane segment, to leave some material to retain the seal strips axially. The individual strip seals are difficult to assemble into the slots at the wall ends of the outer and/or inner ring segments because there are many strips to locate and to retain as the nozzle guide vane arrangement is being built. The seal strips in the EDM slots can become disengaged from one of the nozzle guide vane segments, either during assembly or during transient movements of the nozzle in operation. If this occurs, the seal strip becomes crushed against the wall end surface of the outer or inner ring segment instead of fitting into the slot. This forces adjacent nozzle guide vane segments apart, causing a leak path to open.
A problem to be solved by the present invention is to provide an easy, secure and cost-efficient sealing between nozzle guide vane segments of a nozzle guide vane arrangement. Further a turbine engine shall be provided which allows no or only very marginal performance losses by leakage between adjacent inner and outer platforms of the nozzle guide vane arrangement (s) of the turbine engine.
The problems of the invention are solved by a nozzle guide vane arrangement with the features according to claim 1 and by a turbine engine with the features according to claim 9. Advantages, features, details, aspects and effects of the invention arise from the dependent claims, the description and the figure. Features and details which are described in connection with the nozzle guide vane arrangement count as well for the turbine engine, and vice versa.
According to a first aspect of the present invention the problem is solved by a nozzle guide vane arrangement, in particular of a turbine engine, comprising a plurality of nozzle guide vane segments, whereby a nozzle guide vane segment comprises one or more nozzle guide vane(s) and at a first side of the one or more nozzle guide vane(s) an outer ring segment and/or at the second side of the one or more nozzle guide vane(s) an inner ring segment, whereby adjoining outer ring segments and/or adjoining inner ring segments are sealed by sealing elements , whereby a thin and flexible sealing element is arranged at the outer lateral area of two adjoining outer ring segments, whereby the outer lateral area is that side of an outer ring segment which is averted to the one or more nozzle guide vane(s), and/or a thin and flexible sealing element is arranged at the inner lateral area of two adjoining inner ring segments, whereby the inner lateral area is that side of an inner ring segment which is averted to the one or more nozzle guide vane(s), whereby each sealing element covers the gap between two adjoining outer and/or inner ring segments.
The nozzle guide vane arrangement can be used in a turbine engine, in particular in a gas turbine engine. For better manufacturing and operational purposes the nozzle guide vane arrangement is composed of several nozzle guide vane segments. Each nozzle guide vane segment again has one or more nozzle guide vane(s). Generally two or three nozzle guide vanes are being part of one nozzle guide vane segment. One nozzle guide vane segment comprises at a first side of the one or more nozzle guide vane(s) an outer ring segment and/or at the second side of the one or more nozzle guide vane(s) an inner ring segment. The one or more nozzle guide vane(s) is/are arranged between the outer ring segment and the inner ring segment. The nozzle guide vane segments are arranged to each other, whereby the sum of the nozzle guide vane segments builds the nozzle guide vane arrangement. The nozzle guide vane segments abut against each other at the wall ends of the outer ring segments and the inner ring segments. Therefore the gap or split lines, respectively, between the outer ring segments and/or the inner ring segments have to be sealed by sealing elements. Thus between adjoining outer ring segments and adjoining inner ring segments in each case a thin and flexible sealing element is arranged. The sealing element is thin and flexible and contacts the non-flowpath side of the nozzle guide vane elements, i.e. the radially outwards side of the outer ring segments or the radially inwards side of the inner ring segments. The sealing elements are pressed in place by the cooling air due to the pressure difference of the cooling air pressure and the pressure of a fluid in the main flow path of the nozzle guide vane elements. That means each sealing element is pressed against the non-flowpath side of the nozzle guide vane elements, by which the gap is absolutely sealed.
The arrangement of the thin and flexible sealing elements at the outer lateral area of two adjoining outer ring segments, whereby the outer lateral area is that side of an outer ring segment which is averted to the one or more nozzle guide vane(s) of a nozzle guide vane segment, and/or at the inner lateral area of two adjoining inner ring segments, whereby the inner lateral area is that side of an inner ring segment which is averted to the one or more nozzle guide vane(s) of a nozzle guide vane segment, enables an easy, secure and cost- effective sealing between the nozzle guide vane segments of a nozzle guide vane arrangement. Each sealing element covers the gap or split line, respectively, between the outer and/or inner ring segments of two adjoining nozzle guide vane segments. The outer ring segment of a first nozzle guide vane segment abuts against the outer ring segment of a second nozzle guide vane segment. One thin and flexible sealing element covers the split line between both outer ring segments. The sealing element enables in an easy and cheap way that cooling air can not leak into the main flow path of the nozzle guide vane arrangement at the split line between the outer ring segments of two adjoining nozzle guide ring segments. The same happens at the split line between two adjoining inner ring segments.
According the present invention the sealing element may be thin. "Thin" in respect of the present invention may be defined as a thickness less than a radial width of the inner or outer ring segments. Furthermore the thickness of the sealing element may be a fraction of the other two dimensions of the sealing elements, i.e. the axial length of the sealing element along the gap or the tangential length of the sealing element perpendicular to the gap. To be more precise, the thickness if the sealing element may be a fraction of a millimetre (mm) , in order of a few tenth of a mm. For example the sealing element may have the dimensions of 0.8 mm thick, 10 mm wide and 100 mm long.
According the present invention the sealing element may be flexible. "Flexible" in respect of the present invention may be defined as elastic, bendable, deformable, or adaptive, particularly in a radial direction perpendicular to the gap. This may be provided by a sheet of metal. Furthermore
"flexible" means that a force from air pressure affecting the sealing element is enough to make the seal deform to fit tightly against the ring segments.
A first part of one thin and flexible sealing element is arranged at the outer lateral area of an outer ring segment of a first nozzle guide vane segment and a second part of the same thin and flexible sealing element is arranged at the outer lateral area of an outer ring segment of a second nozzle guide vane segment, so that the sealing element seals the gap between the two adjoining outer ring segments. In the same way another sealing element is arranged at the inner lateral areas of the adjoining inner ring segments.
The arrangement of the sealing elements at the outer lateral area of two adjoining outer and/or inner ring segments can be done very easily. The attachment of the sealing elements can be done very fast, because the outer and inner lateral areas are easily accessible. Furthermore, the sealing can be inspected very easily. Advantageously, the cooling air pressure forces the thin and flexible sealing elements to fit closely against the surface of the nozzle guide vane segments and therefore seals the man flow path through the nozzle guide vane arrangement. According to another advantageous embodiment of the nozzle guide vane arrangement the free ends of an outer ring segment of a nozzle guide vane segment, which are facing the free ends of adjoining outer ring segments of two further nozzle guide vane segments, and/or the free ends of an inner ring segment of a nozzle guide vane segment, which are facing the free ends of adjoining inner ring segments of two further nozzle guide vane segments, are in a straight or curved form.
The sealing elements can be shaped in different ways. The sealing elements can have a flat design. In particular the sealing elements can have a flat, rectangular shape. The length of the sealing elements is similar to the axial length of the inner and/or outer ring segments of the nozzle guide vane segments. Specifically such nozzle guide vane arrange- ments are advantageous for which the sealing elements have a leaf type design. Advantageously, the cross section of the sealing elements is rectangular.
In a very advantageous embodiment of the nozzle guide vane arrangement the nozzle guide vane arrangement is characterized in that each sealing element is attached by attachment elements, e.g. by pins, at the outer lateral area of at least one of the adjoining outer ring segments and/or at the inner lateral area of at least one of the adjoining inner ring segments. Even though the pins do not close all air passages completely and air-tight as a seal, as it would occur for seal strips fitted into slots, the pins will hold the sealing element in position and the perfect sealing will result from the pressure difference of the surrounding fluids. It is advantageous if the sealing element is attached by pins which get through the end walls and the sealing elements together. It is especially advantageous if the pins are arranged ra- dially through the sides of the sealing element and through the sides of the end walls of the ring segments. Both the lateral areas of the free ends of the ring segments of the nozzle guide vane segments and the sealing elements have each at least one hole for guiding at least one pin. Advanta- geously the lateral area of the free ends and as well the sealing elements have two or more holes for receiving two or more pins. The pins are to hold the sealing elements in place when the engine is not operating. During operation the sealing elements are pressed in place by the cooling air pres- sure.
In a specific embodiment, focusing only on a first and an adjacent second ring segment, pin holes may only be provided in the first ring segment. The sealing element may be fixed by attachment elements, e.g. by pins, only to that first ring segment and not to the second ring segment. The sealing element will remain detached - i.e. not physically attached by an attachment element - from the second ring segment but may be in contact to the second ring segment. By these pins, the sealing element will be held in a position to cover the gap. Therefore assembly of the sealing element is simple. During operation, due to the mentioned pressure difference, still all leakage paths will be closed, even though the sealing element is not fixed to the second ring segment.
With the pinned sealing elements, in particular the pinned leaf-type sealing elements, there are no loose small parts to be controlled. Very advantageously are nozzle guide vane arrangements whereby the surfaces of the free ends of the nozzle guide vane segments are ground or milled. Such sealing surfaces can be manufactured fast and cheap and can be very easily being inspected. The surface finish of a ground or milled surface is much smoother so there will be less leakage between such a surface and a corresponding sealing element. A ground or milled surface provides a better sealing then the current EDM-surface. Furthermore, ground or milled surfaces are easier to inspect. The sealing element can not force the nozzle guide vane segments out of position.
The sealing elements do not have to stop short at the forward and aft ends of the nozzle guide vane segment to leave some material to retain the sealing elements axially. In contrast to that the sealing elements cover the edges of two adjoining ring segments of two adjoining nozzle guide vane segments.
Particularly for easier assembly or if the sealing element should be located in a recess to provide an even surface of the non-flowpath surface of the ring segment, the ring segment may have an axial step or ridge or a tilted surface which corresponds to the form of the sealing element.
According to a second aspect of the invention the problem is solved by a turbine engine, in particular a gas turbine engine, comprising one or more nozzle guide vane arrangement (s), whereby at least one nozzle guide vane arrangement is built like a nozzle guide vane arrangement according to the first aspect of the invention. A turbine engine having such a nozzle guide vane arrangement has reduced performance losses. Using such a nozzle guide vane can stop the cooling air from leaking into the main flow path inside the nozzle guide vane arrangement. Because of the specific arrangement of the sealing elements covering the free ends of the adjoining ring segments of two nozzle guide ring segments the gaps between the adjoining nozzle guide vane elements are sealed. The sealing is easy and efficient. It is easy to inspect the surfaces of the free ends where the sealing elements are being fixed. Another advantage of such a nozzle guide vane arrangement is that there is no possibility of the sealing elements to force the nozzle guide vane segments out of position.
The invention will now be described again in detail with ref- erence to the enclosed figure, wherein:
Figure 1 shows schematically two adjoining nozzle guide vane segments, whereby the gap between the outer ring segments of the nozzle guide vane segments is seal- able by a leaf-type sealing element.
Figure 2 shows schematically two adjoining nozzle guide vane segments in a more enlarged view, whereby the gap between the outer ring segments of the nozzle guide vane segments is sealed by a leaf-type sealing ele- ment .
Fig. 1 shows in a schematic way two adjoining nozzle guide vane segments 1 of a nozzle guide vane arrangement, whereby the gap 6 between the outer ring segments 3 of the nozzle guide vane segments 1 is sealed by a leaf-type sealing element 10. Each nozzle guide vane segment 1 can have one or more vanes 2. The nozzle guide vane segment 1 can have an outer ring segment 3 and/or an inner ring segment 4. In this embodiment the nozzle guide vane segments 1 have both an outer 3 and an inner ring segment 4. The vanes 2 are arranged between the outer 3 and inner rings segment 4. The free ends 5 of the rings segments 3, 4 of the two adjoining nozzle guide vane elements 1 directed to a tangential direction of the ring segments 3,4 abut against each other. Between the edges 8 of two adjoining outer ring segments 3 a small gap 6 has to be sealed. This is being done by the sealing element 10 which may cover the free ends 5 of the two adjoining outer ring segments 3 of the nozzle guide vane segment 1. The seal- ing element 10 has advantageously a leaf-type design and fits against the machined surface of the free ends 5 (this will be shown in more detail in Figure 2) . It is held against the machined surface of the free ends 5 by air pressure of the cooling air supply, during operation of the gas turbine. In one of the free ends 5 of the outer ring segments 3 holes 7 are arranged. Further the sealing element 10, which is thin and flexible shaped, has complementary holes 12. After plac¬ ing the sealing element 10 in position the sealing element 10 can be fixed with pins 11 at the free ends 5 of the outer ring segments 3, particularly only at one free end 5 of one of the outer ring segments 3 (but there may be systems available for which a fixation at both free ends 5 of both outer ring segments 3 may be aimed at) . The pins 11 are guided through the holes 12 of the sealing element 10 into the holes 7 of one of the free ends 5 of the outer ring segments 3.
This kind of sealing is an easy and cheap way to close the gap 6 and seal the gap 6 during operation between the abutted ring segments 3, 4.
The sealing is achieved by using a leaf type sealing element 10 that is located outboard of the outer ring segments 3, or inboard of the inner ring segments 4. The sealing elements 10 can be located by pins 11 that attach the thin and flexible sealing element 10 to the sides of each nozzle guide vane segment 1, so there is one sealing element 10 at every gap 6.
The sealing surfaces needed for this invention can be ground or milled which is faster and cheaper than an EDM manufactur- ing process. The sealing surfaces with this invention are very easy to inspect. The free ends 5 may be ground or milled because the surface finish of a ground or milled surface is much smoother so there will be less leakage. Advantageously the free ends 5 and the sides of the sealing element 10 are designed straight and flat. Thus the sealing elements 10 are easy to assemble at the inclined free ends 5 of the ring elements 3, 4. With pinned leaf-type sealing elements 10 there are no separate small parts to control. Figure 2 shows a more detailed view of the gap 6 with an assembled sealing element 10. The proportions may not be accurate and may be exaggerated to show the inventive concept. Again a fraction of a first and a second outer ring segment 3 is shown in an assembled position, leaving the gap 6 in between circumferential ends 19 of the outer ring segments 3. These circumferential ends 19 should be flat surfaces being substantially parallel to each other. Advantageously, no re- cesses are necessary in the surfaces of the circumferential ends 19, so no recesses may be present in the surfaces of the circumferential ends 19.
In a cross section of a radial plane, the nozzle guide vane elements build substantially an annulus through which the main fluid passes during operation. All inner and outer ring segments 3 and 4 build together substantially a circular ring. Now only focusing on the outer ring segments 3, inner surfaces of the outer ring segments 3 build together a sub- stantially cylindrical surface. In a cross section, the inner surfaces build a circle, each outer ring segment 3 having showing an inner circular arc 17. Disregarding the free ends 5, the same is true for outer surfaces of the outer ring segments 3, which form a substantially cylindrical surface par- allel to the inner surface. In a cross section, the outer surfaces build substantially a circle, each outer ring segment 3 having showing an outer circular arc 15.
Only for the free ends 5, according to this embodiment, the shape of the outer circular arc may be not followed anymore by the outer surface. The outer surface may be flattened. It has to be noted that this may be considered an optional embodiment that is not necessary in all embodiments, but may have advantages depending on the dimensions of the sealing element.
On the outer surface, starting from an axial ridge 18, a flat tilted surface 20 starts leading to a reduced material thick- ness of the outer ring segment 3 in direction of the circumferential end 19. In a cross section, the flat tilted surface 20 results in a straight line 16, so that the overall cross section of the outer surface of a single outer ring segment 3 is a" circular arc segment 15 with straight lines 16 at both free ends 5 of the outer ring segment 3.
Advantageously, once assembled the flat tilted surface 20 of a first outer ring segment 3 should be substantially in the same plane as the flat tilted surface 20 of a second outer ring segment 3, as indicated in Figure 2. This allows that the sealing element 10 can be attached in such a way that the sealing element 10 will cover the gap 6 completely and will stay in loose contact with a first tilted surface 20 of the first outer ring segment 3 and with a second tilted surface 20 of the second outer ring segment 3.
Figure 2 shows that the sealing element 10 is attached to the flat tilted surfaces 20. Preferably the sealing element 10 is bolted via pins 11 merely to the first tiled surface 20 of the first outer ring segment 3. The pins will hold the sealing element 10 in position. Preferably the sealing element 10 is not attached to the second tilted surface 20 of the second outer ring segment 3. The sealing element 10 covers the gap 6. If the gas turbine is not in operation, may block a substantial amount of fluid but is not a perfect seal. Fluid may pass through the gap 6. But during operation of the gas turbine, a pressure difference will be utilized, in which a first fluid pressure radially outwards of the outer ring seg- ments 10 - the fluid being for example cooling air - is higher than the pressure of a second fluid through the main flow path radially inwards of the outer ring segments 10. This pressure difference leads to a force on the sealing element 10 directed radially inwards, so that the sealing ele- ment 10 will be in firm contact with both flat tilted surfaces 20 which are opposite to the sealing element 10. Thus, the sealing element 10 provides a sealing of the gap 6 due to the pressure difference, due to the form of the surfaces, and due to the flexibility of the sealing element 10.
It has to be noted, that Figure 2 is only a schematical draw- ing. The sealing element 10 may exceed over the ridge 18 or over the axial ends - e.g. indicated by the straight line 16 - of the ring segments 3,4. The pins 11 may be one form of attaching the sealing element 10 to the ring segments 3,4. There may be other ways of attaching the sealing element 10, as long it holds the sealing element 10 substantially in position and keeps the sealing element 10 close to the flat tilted surfaces 20. Therefore, as an easy solution, two pins 11 for attaching one side of the sealing element 10 to one of the flat surfaces 20 is proposed. A higher number of pins may be also possible or different means of attachment.
For the outer ring segments 3, a flat surface can be gained at the free ends 5 by a reduction of material approaching the gap 6, e.g. by specifically casting the nozzle guide vane element in this form or by machining away material on the outside surface in the area of the free ends 5. It has to be pointed out, that this reducing of the thickness of the outer ring segment 3 may only be minimal, e.g. 0.1 to 0.2 mm.
Therefore the form of the outer ring segment 3 may be consid- ered completely cylindrical.
To gain the flat surface at the free ends 5, also material could be applied to the free ends 5, specifically in the direction directed away from the gap 6.
Especially with a large radius, the surfaces may be considered substantially flat and no special treatment of the free ends 5 is necessary. They may be cylindrical as the remaining parts of the outer ring segment 3, without leading to nega- tive side effects.
Figure 2 may specifically apply to outer ring segments 3. For inner ring segments 4, to which the sealing element 10 will be applied from the radially inner surface, it may be advantageous to not have a flattened surface but to keep the cylindrical shape over the whole expanse of the ring segment 4. The reason is that the sealing element 10, when attached to a free end 5 of a first inner ring segment 4 will automatically be pressed to the opposing free end 5 of a second inner ring segment 4 due to the curvature, which is directed inwardly. Alternatively, a flat surface could be achieved on the inner surface of the inner ring segment 4 with a thinner section in the area of the free end 5 that is directed away from the gap 6. Alternatively, material could be added on the inner surface of the inner ring segment 4 close to the gap 6.
The sealing element 10 is designed to be flexible to adapt its form as a response to adjacent air pressure differences. Even though this might ideally be happening for a foil like thin cuboid, different shapes may be anticipated. For example the cross sections in direction from one free end 5 to another free end 5 may be slightly trapezoid, triangular, or convex, as long as the sealing element 10 remains flexible.
As already be mentioned, depending on the flexibility of the sealing element 10 and based on the radius of the ring segments 3,4, it may be advantageous if the free ends 5 will be narrowing or widening the thickness of the ring segments 3,4 from the side to which the sealing element 10 will be applied. Alternatively it may be advantageous if the thickness of the ring segments 3,4 will stay constant. Not shown in the figure, a larger contact pressure per surface area could be gained, if the ring segment end to which the seal is not attached had a ridge for the sealing element to rest on. If the material of the sealing element was wear resistant but still flexible it may reduce the leakage fur- ther.

Claims

Claims
1. Nozzle guide vane arrangement, in particular of a turbine engine, comprising a plurality of nozzle guide vane segments (1) , whereby a nozzle guide vane segment (1) comprises one or more nozzle guide vane(s) (2) and at a first side of the one or more nozzle guide vane(s) (2) an outer ring segment (3) and/or at the second side of the one or more nozzle guide vane(s) (2) an inner ring segment (4), whereby adjoining out- er ring segments (3) and/or adjoining inner ring segments (4) are sealed by sealing elements (10), characterized in that a thin and flexible sealing element (10) is arranged at the outer lateral area of two adjoining outer ring segments (3), whereby the outer lateral area is that side of an outer ring segment (3) which is averted to the one or more nozzle guide vane(s) (2), and/or a thin and flexible sealing element (10) is arranged at the inner lateral area of two adjoining inner ring segments (4), whereby the inner lateral area is that side of an inner ring segment (4) which is averted to the one or more nozzle guide vane(s) (2), whereby each sealing element (10) covers the gap (6) between two adjoining outer (3) and/or inner ring segments (4).
2. Nozzle guide vane arrangement according to claim 1, char- acterized in that each sealing element (10) is shaped like a substantially flat sheet.
3. Nozzle guide vane arrangement according to claim 1 or 2, characterized in that the free ends (5) of an outer ring seg- ment (3) , which are facing the free ends (5) of adjoining outer ring segments (3) , and/or the free ends (5) of an inner ring segment (4), which are facing the free ends (5) of adjoining inner ring segments (4), are in a straight or curved form.
4. Nozzle guide vane arrangement according to one of the claims 1 to 3, characterized in that the sealing elements (10) are leaf type sealing elements.
5. Nozzle guide vane arrangement according to one of the claims 1 to 4, characterized in that the cross section of the sealing elements (10) is rectangular.
6. Nozzle guide vane arrangement according to one of the claims 1 to 5, characterized in that each sealing element (10) is attached by an attachment element, in particular by pins (11), at the outer lateral area of at least one of the adjoining outer ring segments (3) and/or at the inner lateral area of at least one of the adjoining inner ring segments (4), the pins (11) being particularly adapted to correspond to holes (12) in the sealing element (10) and to holes (7) in the outer lateral area of at least one of the adjoining outer ring segments (3) and/or in the inner lateral area of at least one of the adjoining inner ring segments (4).
7. Nozzle guide vane arrangement according to one of the claims 1 to 6, characterized in that each sealing element
(10) is attached by an attachment element at the outer lateral area of a first one of the adjoining outer ring segments
(3) and remains detached to the outer lateral area of a second one of the adjoining outer ring segments (3)
and/or
each sealing element (10) is attached by an attachment element at the inner lateral area of a first one of the adjoining inner ring segments (4) and remains detached to the inner lateral area of a second one of the adjoining inner ring segments (4 ) .
8. Nozzle guide vane arrangement according to one of the claims 2 to 7, characterized in that the surfaces of the free ends (5) are ground or milled.
9. Turbine engine, in particular gas turbine engine, comprising one or more nozzle guide vane arrangement (s) , characterized in that at least one nozzle guide vane arrangement is build like a nozzle guide vane arrangement according to one of the claims 1 to 8.
PCT/EP2009/007479 2009-10-19 2009-10-19 Nozzle guide vane arrangement and turbine engine WO2011047693A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
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Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/EP2009/007479 WO2011047693A1 (en) 2009-10-19 2009-10-19 Nozzle guide vane arrangement and turbine engine

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WO2011047693A1 true WO2011047693A1 (en) 2011-04-28

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Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8834109B2 (en) 2011-08-03 2014-09-16 United Technologies Corporation Vane assembly for a gas turbine engine
US8894365B2 (en) 2011-06-29 2014-11-25 United Technologies Corporation Flowpath insert and assembly
EP3179046A1 (en) * 2015-12-11 2017-06-14 General Electric Company Cmc thermal clamps
US11415005B2 (en) 2019-10-09 2022-08-16 Rolls-Royce Plc Turbine vane assembly incorporating ceramic matrix composite materials
EP4086435A1 (en) * 2021-05-03 2022-11-09 Raytheon Technologies Corporation Variable thickness machinable coating for platform seals
US11591921B1 (en) 2021-11-05 2023-02-28 Rolls-Royce Plc Ceramic matrix composite vane assembly
US11732596B2 (en) 2021-12-22 2023-08-22 Rolls-Royce Plc Ceramic matrix composite turbine vane assembly having minimalistic support spars

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2472062A (en) * 1943-08-24 1949-06-07 Jarvis C Marble Turbine casing construction
US4921401A (en) * 1989-02-23 1990-05-01 United Technologies Corporation Casting for a rotary machine
GB2262573A (en) * 1991-12-18 1993-06-23 Snecma Turbine casing assembly.
US20020187040A1 (en) * 2001-06-06 2002-12-12 Predmore Daniel Ross Overlapping interference seal and methods for forming the seal
EP1431515A2 (en) * 2002-12-20 2004-06-23 General Electric Company Turbine engine shroud segment and assembly with circumferential seal on a planar segment surface
EP1431518A2 (en) * 2002-12-20 2004-06-23 General Electric Company Turbine engine shroud segment assembly with a surface-recessed seal bridging adjacent shroud segments

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2472062A (en) * 1943-08-24 1949-06-07 Jarvis C Marble Turbine casing construction
US4921401A (en) * 1989-02-23 1990-05-01 United Technologies Corporation Casting for a rotary machine
GB2262573A (en) * 1991-12-18 1993-06-23 Snecma Turbine casing assembly.
US20020187040A1 (en) * 2001-06-06 2002-12-12 Predmore Daniel Ross Overlapping interference seal and methods for forming the seal
EP1431515A2 (en) * 2002-12-20 2004-06-23 General Electric Company Turbine engine shroud segment and assembly with circumferential seal on a planar segment surface
EP1431518A2 (en) * 2002-12-20 2004-06-23 General Electric Company Turbine engine shroud segment assembly with a surface-recessed seal bridging adjacent shroud segments

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8894365B2 (en) 2011-06-29 2014-11-25 United Technologies Corporation Flowpath insert and assembly
US8834109B2 (en) 2011-08-03 2014-09-16 United Technologies Corporation Vane assembly for a gas turbine engine
EP3179046A1 (en) * 2015-12-11 2017-06-14 General Electric Company Cmc thermal clamps
CN106917644A (en) * 2015-12-11 2017-07-04 通用电气公司 CMC calorifics clips
US10428665B2 (en) 2015-12-11 2019-10-01 General Electric Company CMC thermal clamps
US11415005B2 (en) 2019-10-09 2022-08-16 Rolls-Royce Plc Turbine vane assembly incorporating ceramic matrix composite materials
EP4086435A1 (en) * 2021-05-03 2022-11-09 Raytheon Technologies Corporation Variable thickness machinable coating for platform seals
US12000288B2 (en) 2021-05-03 2024-06-04 Rtx Corporation Variable thickness machinable coating for platform seals
US11591921B1 (en) 2021-11-05 2023-02-28 Rolls-Royce Plc Ceramic matrix composite vane assembly
US11732596B2 (en) 2021-12-22 2023-08-22 Rolls-Royce Plc Ceramic matrix composite turbine vane assembly having minimalistic support spars

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