EP2811118A1 - Guide blade segment of a turboengine and turbine - Google Patents

Abstract

The present invention relates to a stator segment (100) of a turbomachine, having an upstream housing-side suspension (1) and / or a downstream housing-side suspension (3) and a platform (5), wherein the suspensions are arranged on the platform (5) and the Platform (5) has a first sealing portion (17), and wherein the platform (5) via a connecting portion (15) which connects the rear (3) suspension with the platform (5), extends in the flow direction, and wherein the first seal portion (17) located in a portion (18) downstream of the connection portion (15) has a first slot (19) which is continuous in the circumferential direction. The present invention further relates to a turbine having at least one vane segment (100).

Description

The present invention relates to a stator segment of a turbomachine with an upstream and / or a downstream housing-side suspension and a platform according to the preamble of claim 1. Furthermore, the present invention relates to a turbine, in particular a gas turbine, according to the preamble of claim 10.

In turbomachines, vanes can be fastened to the housing in different ways. Typically, attachment is by means of upstream and downstream housing hanger connected to a vane platform from which the vane extends. Depending on the configuration of the housing suspensions and the vane platform, sealing elements may be integrated into individual vane segments to seal gaps or gaps that exist between adjacent vane segments. As a result, a seal of the flow channel with respect to the housing cavities is to be achieved.

An object of the present invention is to propose a further stator segment of a turbomachine with at least one first sealing section. Furthermore, it is an object of the present invention to propose a turbine with at least one vane segment.

The object of the invention is achieved by the vane segment with the features of claim 1. It is further achieved by a turbine having the features of claim 10.

According to the invention, therefore, a stator segment of a turbomachine is proposed, which has an upstream, or front, and a downstream, or rear, housing-side suspension and a platform. Alternatively, the Guide vane segment either an upstream or a downstream, housing-side suspension and a platform.

The suspensions are arranged on the platform. For example, the upstream chassis-side suspension may be located in the front portion of the platform and the downstream-side suspension in the rear portion of the platform.

The platform has a first sealing portion.

Further, the platform extends beyond a connection region connecting the rear suspension to the platform with respect to the flow direction in use of the vane segment.

The first sealing portion, which lies in a portion downstream of the connecting region, according to the invention has a first slot, which is continuous in the circumferential direction.

In all the above and following embodiments, the use of the term "may be" or "may have" etc. is synonymous with "preferably" or "preferably has", etc., and is intended to explain embodiments of the invention.

Whenever numerical words are mentioned herein, those skilled in the art will understand these as indicating a numerically lower limit. If this does not result in a contradiction that is recognizable to the person skilled in the art, the person skilled in the art therefore always reads "at least one" or "at least one", for example, when specifying "a" or "one". This understanding is also encompassed by the present invention as the interpretation that a numerical word such as "a" may alternatively be meant as "exactly one" wherever technically possible for those skilled in the art. Both are encompassed by the present invention and apply to all number words used herein. Advantageous developments of the present invention are the subject of subclaims and embodiments.

Embodiments of the invention may have one or more of the following features in any combination.

In some embodiments according to the invention, the turbomachine is a compressor or a turbine, in particular a gas turbine.

The term "vane segment" as used herein, in some embodiments of the invention, refers to an assembly or segment having one or more vanes and / or optionally optionally provided further sections (or elements, segments, parts) associated with the invention or the guide vanes are connected.

In some embodiments of the invention, a vane segment is a vane cluster. A Leitschaufelcluster may have a plurality of guide vanes, in particular three vanes, at least one, but usually two housing-side suspensions and at least one platform. A vane may have at least one vane profile with a pressure and a suction side and a respective front and rear blade edge.

As used herein, the term "downstream enclosure-side suspension" refers to a suspension that is located farther downstream in the direction of flow than an upstream or forward, further upstream suspension. The flow direction can be referred to as the axial direction of the longitudinal axis of the turbomachine. Perpendicular to the axial direction is the radial direction. In a plane perpendicular to the axial direction, the circumferential direction.

In some embodiments of the invention, the first sealing portion is a groove or a recess, hereinafter referred to as a groove. A groove may have a U-profile in cross-section (perpendicular to the longitudinal direction). A groove may have a rectangular, polygonal, semicircular or other cross-sectional shape.

In some embodiments according to the invention, the groove can be prepared and / or configured and / or configured for receiving a sealing element, for example a sealing plate, or have a sealing element. The sealing plate can z. B. inserted into the groove, inserted, clamped or connected in a manner with the groove or be. The sealing portion may effect communication between adjacent vane segments. The sealing function of the sealing portion may be completely or at least partially fulfilled after the insertion of the sealing sheet. The sealing function can serve to seal the flow channel in the direction of the cavities or with respect to the cavities of the housing of the turbomachine in the vane region.

The first, as well as other sealing portions may be referred to as sealing segments.

In certain embodiments of the invention, the sealing portion is a receiving device or receiving device for a sealing plate or a plug-in sealing device.

As used herein, the term "connecting region connecting the rear suspension to the platform" in some embodiments of the invention designates the hub, joint, connecting portion or transition region between the downstream rearward housing-side suspension and the platform. The lug may be made together with the suspension and the platform as a part or section, in particular made as a casting. The casting may be referred to as an integral casting that collectively fulfills the function of the suspension, the platform, and the connection area (or transition area).

In certain embodiments according to the invention, the connection region has an increased accumulation of material, for example due to structurally necessary rounding and / or material reinforcements in the connection region.

In some embodiments of the invention, the upstream suspension has a second sealing portion and the downstream suspension has a third sealing portion.

In some embodiments according to the invention, the first and / or the second and / or the third sealing section is designed for inserting sealing sheets or has sealing sheets. In particular, the three sealing sections (first, second and / or third sealing section) can be arranged in such a way and have sealing sheets such that a sealing of the housing cavities with respect to the throughflow region of the turbomachine is achieved.

In certain embodiments of the invention, the platform and the first seal portion extend downstream of the connection region beyond a vane profile trailing edge in the flow direction. The vane segment may include one or more vanes. The extent of the platform and the first sealing portion may refer to one or more vanes. Although the vane segment has a plurality of guide vanes, it is contemplated according to the invention that the extent does not concern all the vanes, but is provided only with one or less than all vanes.

In some embodiments of the invention, the first sealing portion of the platform extends completely or partially beyond the connecting portion of the rear suspension to the platform. Although only partially extending, the platform has a first sealing portion, but this does not extend beyond the connecting portion of the rear suspension.

In some embodiments of the invention, the portion of the platform has a second slot downstream of the connection area. The second slot may be continuous in the radial direction, for example, to the outside. A radially inwardly outwardly continuous second slot is an outgoing from the first slot and in communication with this, outward (ie open in cavities of the housing) continuous or open slot.

In some embodiments of the invention, the portion of the platform downstream of the connection region has a second slot that is continuous inward in the radial direction alone. A radially inwardly continuous second slot is in this embodiment, from the first slot to the inside (up to the flow area of the turbomachine open) continuous slot.

In certain embodiments, however, the portion of the platform downstream of the connection region has a second slot that is radially outwardly and inwardly continuous.

With a second slot, the stiffness of the vane segment, in particular in the connection region between the rear suspension and the platform, can be advantageously reduced.

The second slot may have a square, rectangular, trapezoidal, oval or other cross section in a plane perpendicular to its longitudinal axis. The longitudinal axis may be arranged in the circumferential direction straight or obliquely (diagonally) with respect to the circumferential and flow direction.

In some embodiments of the invention, the portion of the platform that lies downstream of the connection region has a third slot that is continuous in the circumferential direction. For example, the second slot is disposed at one end (with respect to the circumferential direction) of the aforementioned portion, the third slot at the other end. Thus, at both ends of the section in the circumferential direction more Leitschaufelsegmente be arranged.

In some embodiments according to the invention, the portion of the platform downstream of the connecting region has a sectionally tapered wall thickness, ie a narrowing wall thickness. The wall thickness can taper in the radial direction and / or in the circumferential direction.

In certain embodiments of the invention, the vane segment has at least two vanes. A vane segment having at least two vanes may be referred to as a vane cluster. The vane cluster may in particular have three guide vanes.

In certain embodiments of the invention the vane segment is manufactured as a casting, in particular as an integral casting, in particular in one piece. As an integral casting, a casting may be referred to as having multiple functional parts or sections. An integral vane segment may include one or more vanes, further comprising front and / or rear chassis side hangers, and a platform. A vane segment, which is produced as a casting, is reworked, for example ground, in particular at the abutment surfaces to adjacent further vane segments. Furthermore, provided sealing sections cast guide vane segment can be reworked.

The sealing portions are produced or reworked by means of erosion in some embodiments according to the invention.

Some or all embodiments according to the invention may have one, several or all of the advantages mentioned above and / or below.

In the manufacture of turbomachines according to the state of the art, in particular of gas turbines, connection points or joints of guide blade segments, in particular of guide blade clusters, can be sealed with the aid of sealing sheets. For this purpose, sealing sections, sealing grooves or sealing slots can be introduced into the abutting surfaces in the hub and housing region of the gas turbines, in which the sealing plates are inserted during assembly of the turbomachine. As a result, the sealing of the gas or flow channel in the direction of the housing cavities in the vane region can take place. In the connecting region of the rear, housing-side suspension with the platform of the guide blade segment may result from structurally related reinforcements, for example, by applying material to abutting edges, which lead to rounding, an increase of material result. This can become one Increase in stiffness in this area, which may have a negative effect on the tolerable thermomechanical load cycles in the area of the pressure-side blade trailing edge and may result in unintentional early failure of the component according to the prior art.

A reduction of the rigidity in the embodiment of the guide blade segment can be accompanied or achieved with a reduction of the sealing sheet length. As a result, however, the gap seal may decrease or decrease, which may result in an increase in leakage losses. Thus there is a conflict between on the one hand the sealing effectiveness and on the other hand the sustainable load changes at the considered place.

By means of the first slot according to the invention, which has the first sealing section of the guide blade segment according to the invention, a reduction of the rigidity of the guide blade segment, in particular in the connection region of the rear, housing-side suspension with the platform, can be advantageously achieved. A reduction in the rigidity-and thus indirectly an increase in the load cycles sustained in the operation of the turbomachine-can advantageously be achieved by a vane segment according to the invention (because of the integration of sealing sections as narrow webs at the joint of the outside of the rear platform). Furthermore, the extension or continuation of the sealing sheets or their trailing edges beyond the guide blade trailing edges can advantageously improve the sealing of the housing cavities in the region of the rear platform (reduction of the thermal entry into the rear housing suspension or the possibility of using less cooling air).

Fig. 1

zeigt eine perspektivische Ansicht eines Ausschnitts eines erfindungsgemäßen Leitschaufelsegments;

Fig. 2

zeigt eine weitere perspektivische Ansicht des in Fig. 1 gezeigten erfindungsgemäßen Leitschaufelsegments;

Fig. 3a

zeigt einen Detailausschnitt einer perspektivischen Ansicht eines weiteren erfindungsgemäßen Leitschaufelsegments mit einem ersten Schlitz;

Fig. 3b

zeigt eine weitere perspektivische Ansicht des in Fig. 3a gezeigten erfindungsgemäßen Leitschaufelsegments;

Fig. 4a

zeigt einen Detailausschnitt einer perspektivischen Ansicht eines wiederum weiteren erfindungsgemäßen Leitschaufelsegments; und

Fig. 4b

zeigt eine weitere perspektivische Ansicht des in Fig. 4a gezeigten wiederum weiteren erfindungsgemäßen Leitschaufelsegments.

The present invention will be explained in the following with reference to the accompanying drawings, in which identical reference numerals designate identical or similar components, by way of example. In each schematically simplified figures:

Fig. 1

shows a perspective view of a section of a guide vane segment according to the invention;

Fig. 2

shows another perspective view of the in Fig. 1 shown guide vane segment according to the invention;

Fig. 3a

shows a detail of a perspective view of another vane segment according to the invention with a first slot;

Fig. 3b

shows another perspective view of the in Fig. 3a shown guide vane segment according to the invention;

Fig. 4a

shows a detail of a perspective view of yet another guide vane segment according to the invention; and

Fig. 4b

shows another perspective view of the in Fig. 4a in turn shown further guide vane segment according to the invention.

Fig. 1 shows a perspective view of a section of a guide vane segment 100 according to the invention.

The vane segment 100 according to the invention comprises an upstream housing-side suspension 1, a downstream housing-side suspension 3, a platform 5, and three guide vanes 200.

Each vane 200 has a pressure side 7, a rear suction side 9 (obscured), a vane leading edge 11, and a vane trailing edge 13.

A connection region 15 connects the rear suspension 3 to the platform 5, which merge into one another in the connection region 15.

Further shows Fig. 1 a first sealing portion 17 which extends into a portion 18 downstream of the connecting portion 15 inside. The first sealing section 17 is designed or manufactured in the section 18 as the first slot 19. The first slot 19 is continuous in the circumferential direction z.

In addition to the first sealing portion 17 in the platform 5, the blade assembly 100 has a second sealing portion 17a in the upstream suspension 1 and a third sealing portion 17b in the downstream suspension 3.

In the sealing portions 17, 17a, 17b sealing plates can be inserted. By means of these sealing plates, the joints or joints to other sealing portions in adjacent vane segments (in Fig. 1 not shown) bridged and sealed with it. In addition to the function of sealing the flow channel between the guide vanes, these sealing sheets can also fulfill a thermal sealing function, or thermal insulation, in the form of a heat shield. The sealing plates can thus fulfill an integral function with regard to the flow-related and the temperature-related sealing function between the flow channel and the housing.

The sealing plate, which is inserted into the first sealing portion 17, may extend into the portion 19 of the platform 5. This sealing plate can extend in the circumferential direction of the first slot 19 either only over part of the entire slot depth (eg corresponding to the depth of the first sealing section 17 in the circumferential direction), over the entire slot depth, or over the entire slot depth. The rigidity of the section 18 is influenced accordingly. For example, the rigidity is smaller with a small depth of the sealing plate in the circumferential direction.

Fig. 2 shows another perspective view of the in Fig. 1 shown guide vane segment 100 according to the invention.

The first slot 19 is continuous in the section 18 in the circumferential direction z.

Fig. 3a shows a detail of a perspective view of another guide vane segment 100 according to the invention with a second slot 20, which in both the radial direction y and in the circumferential direction z is open or continuous.

Fig. 3b shows another perspective view of the in Fig. 3a shown further guide vane segment 100 according to the invention.

Fig. 4a shows a detail of a perspective view of yet another guide vane segment 100 according to the invention.

The first slot 19 extends in the flow stream x shortened in the section 18, compared with its extension in Fig. 1 and Fig. 2 , As a result of this reduction, the wall thickness 21 is made narrower in the radial direction y with respect to the wall thickness 23 with the slot 19. Thus, the rigidity of the portion 18 can be advantageously reduced.

Fig. 4b shows another perspective view of the in Fig. 4a shown further guide vane segment 100 according to the invention.

LIST OF REFERENCE NUMBERS

reference numeral description 100 vane segment 200 vane x The direction of flow; axially y radial direction z circumferentially 1 upstream, front housing-side suspension 3 downstream, rear-side suspension 5 platform 7 Pressure side of the vane 9 Suction side of the vane 11 vane leading edge 13 vane trailing 15 Connection area; connects the rear suspension with the platform 17 first sealing section 17a, 17b second / third sealing section 18 Section of the platform downstream of the connection area 19 first slot 20 second slot 21 Wall thickness in the radial direction without sealing section 23 Wall thickness in the radial direction with sealing section

Claims (10)

Guide vane segment (100) of a turbomachine, with an upstream housing-side suspension (1) and / or a downstream housing-side suspension (3) and a platform (5), wherein the suspensions (1, 3) on the platform (5) are arranged the platform (5) has a first sealing portion (17), and wherein the platform (5) extends in the flow direction beyond a connecting region (15) which connects the rear suspension (3) to the platform (5),
characterized in that
the first sealing portion (17) located in a portion (18) downstream of the connecting portion (15) has a first slot (19) which is continuous in the circumferential direction. The vane segment (100) according to claim 1, wherein the upstream suspension (1) has a second seal portion (17a) and the downstream suspension (3) has a third seal portion (17b). Guide vane segment (100) according to claim 1 or 2, wherein the first, the second and / or the third sealing portion (17, 17a, 17b) are formed for inserting sealing plates or sealing plates. A vane segment (100) according to any one of the preceding claims, wherein the platform (5) and the first seal portion (17) extend downstream of the connection region (15) beyond a vane profile trailing edge (13) in the flow direction. A vane segment (100) according to any one of the preceding claims, wherein the portion (18) of the platform (5) has downstream of the connection region (15) a second slot (20) which is radially outwardly and / or inwardly continuous. A vane segment (100) according to any one of the preceding claims, wherein the portion (18) of the platform (5) downstream of the connection region (15) has a third slot which is continuous in the circumferential direction. Guide vane segment (100) according to one of the preceding claims, wherein the portion (18) of the platform (5) downstream of the connecting region (15) has a sectionally tapered wall thickness (21). The vane segment (100) of any one of the preceding claims, wherein the vane segment (100) comprises at least two vanes (200). A vane segment (100) according to any one of the preceding claims, wherein the vane segment (100) is made as a casting. Turbine, characterized by at least one vane segment (100) according to one of the preceding claims.

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