DE102019211815A1 - Turbomachine Blade - Google Patents

Abstract

The present invention relates to a blade for a turbo machine, in particular a compressor or turbine stage of a gas turbine, in particular an aircraft engine, the blade having at least one airfoil profile (100; 200), which has a leading edge (101; 201), a trailing edge (102; 202 ), a pressure side (103; 203) and suction side (104; 204) connecting them, and at least one shroud (10; 20) which has an upper side (11; 21) facing the airfoil, an underside (12) remote from the airfoil, and a front and a rear axial end face (13, 14; 23, 24) and a pressure-side side surface (15; 25) which connects the top and bottom and the two axial end faces, and a suction-side side surface (16; 26) which Connect the top and bottom and the two axial end faces, with at least one, in particular slot-like, recess (30, 40; 50, 60) in at least one of these side faces for partial A is arranged receiving a sealing element (1).

Description

The present invention relates to a blade for a turbomachine, in particular a compressor or turbine stage of a gas turbine, a blade arrangement with at least two blades, a sealing element for such a blade (arrangement) and a turbo machine, in particular a gas turbine, with the blade arrangement and a method of operation the turbo machine.

From the U.S. 5,531,457 A a blade arrangement is known in which a gap between adjacent shrouds is sealed over the entire profile depth of the blade by a so-called “feather seal”. For cooling, small channels surrounding the sealing elements are formed in the slots in which these sealing elements are inserted, in order to blow cooling air past the sealing elements onto the upper side of the shrouds.

One object of an embodiment of the present invention is to improve a turbomachine, in particular its operation and / or manufacture.

This object is achieved by a turbomachine blade with the features of claim 1. Claims 5, 6, 11 and 13 provide a blade assembly with at least two of the blades described here, a sealing element for a blade (assembly) described here, a turbomachine with one or more of the blade assemblies described here and a method for operating such a turbomachine under protection. Advantageous embodiments of the invention are the subject of the dependent claims.

According to one embodiment of the present invention, one or more blades for one or a turbo machine, in one embodiment the compressor or turbine stage of a gas turbine, in particular an aircraft engine, or one or more blade arrangements for the turbo machine each have a blade with at least one Airfoil profile, which has a leading edge or profile nose, a trailing edge, a pressure side connecting these and a suction side connecting the leading and trailing edges. This airfoil profile, to which reference is made below, can in particular be an airfoil profile next to the shroud to which reference is made below, an airfoil profile at half the airfoil or thread axis height or the like.

According to one embodiment of the present invention, the blade (each) has at least one shroud, in a development two shrouds that are radially spaced from one another. The shroud to which reference is made below can in particular be a radially inner or outer shroud or a shroud closest to the blade tip or root. In one embodiment, it is cohesively connected to the blade (profile) or formed integrally with it.

According to one embodiment of the present invention, the shroud, in a further development both shrouds in each case, has an upper side facing the airfoil, an underside facing away from the airfoil, a front axial end face, a rear axial end face as well as a pressure side side surface, which this upper and lower side and these two axial end sides connects, and a suction side side surface that connects these top and bottom and these two axial end faces.

According to one embodiment of the present invention, at least one recess or depression is arranged or formed in at least one of these two side surfaces, in a further development both side surfaces, which in the assembled or operating state of the blade (arrangement) one or more (each) one-part or multi-part sealing element (s) partially accommodates or provided for this purpose, in particular set up, is or is used and in the present case is also referred to as the first recess without loss of generality. This or one of these (one-part or multi-part (s)) sealing element (s), which is partially received in the or such a first recess or provided for this purpose, in particular set up, is or is used, is correspondingly present without restriction of the Generally also referred to as (a) first sealing element.

According to an embodiment of the present invention, in at least one of these side surfaces in which the or one of the first recess (s) is arranged or formed, in a further development both side surfaces are each, in addition to this first recess, at least one further recess or recess arranged or formed, which in the assembly or operating state of the blade (arrangement) partially receives one or more further (each) one or more part (s) sealing element (s) or is provided for this purpose, in particular set up , is or is used. This or one of these (one-part or multi-part (s)) sealing element (s), which is partially received in this or such a further recess or provided for this purpose, in particular set up, is or is used, is correspondingly present without restriction of the General also referred to as (a) further sealing element.

As a result, in one embodiment between the or at least partially in the The sealing element (s) received in the first paragraph and the sealing element (s) at least partially received in the further paragraph are advantageously provided with a free radial gap through which the coolant, in particular cooling air, can flow from the underside of the shroud to the upper side of the shroud and advantageously cool it .

In one embodiment, the or one or more of the first and / or further recess (s) or depressions is / are each slot-like, in particular -shaped or as a slot, in particular as a slot in the axial direction, educated. As a result, the (respective) sealing element can be guided or held better in one embodiment and / or a sealing effect can be improved.

According to one embodiment of the present invention, the or one or more of the first and / or further recess (s) each have at least one shoulder on which in an axial direction from the front to the rear axial end face (coming or seen) a recess depth, in particular a maximum, minimum or mean distance between a bottom or base of the recess and its edge in the side surface, reduced, in one embodiment of the present invention an axial, in particular maximum, minimum or average distance of this rear shoulder of the or one or more of the first recess (s) from the front edge of the airfoil profile of the (respective) blade at least 40%, in one embodiment at least 50%, and at most 100%, in one embodiment at most 90%, of an axial profile depth and this paragraph is therefore referred to as the rear paragraph (of the corresponding (first or further) recess) w earth.

As a result, in one embodiment, a free radial gap can advantageously be provided behind the shoulder, through which coolant, in particular cooling air, can flow from the underside of the shroud to the upper side of the shroud and can advantageously cool it.

This is based, in particular, on the surprising finding that a radial gap, the beginning of which is defined by such a shoulder, does not have to be covered by a feather seal, so that compared to the one mentioned above U.S. 5,531,457 A In one embodiment, the manufacturing effort can be reduced and / or the cooling and / or reliability can be improved.

In one embodiment, the axial direction is directed or oriented parallel to a (main) machine axis or axis of rotation of the turbo machine, in particular from a turbo machine inlet to a turbo machine outlet or in the flow direction. Accordingly, in the present case in particular downstream (right) elements or positions are referred to as rear elements or positions, and upstream (right) elements or positions as front elements or positions. In one embodiment, the circumferential direction is a direction of rotation about this axis of rotation, and in one embodiment is a radial direction perpendicular to the axial and circumferential direction, in particular directed or oriented away from the axis of rotation. In one embodiment, the axial profile depth is the axial distance between the leading edge or profile nose and the rear edge, in particular an axially foremost and rearmost point of a skeleton or (profile) center line of the airfoil profile.

In one embodiment, the or one or more of the first and / or further recess (s) ends in the axial direction from the front to the rear axial face at the rear shoulder of this recess, in According to a further development, the side face has a section which adjoins this rear shoulder in the axial direction and is free of cutouts or depressions, in particular a flat or planar section.

As a result, in one embodiment, a particularly advantageous free radial gap can be made available behind the shoulder and, in particular, the cooling and / or reliability can be (further) improved.

In one embodiment, the recess depth of the or one or more of the first and / or further recess (s) on the rear shoulder of this recess is reduced to a maximum of 75%, in one embodiment to a maximum of 25%, in particular a maximum, minimum or average recess depth up to the shoulder. As a result, in one embodiment, part of an air flowing through the free radial gap can be guided axially and thus advantageously blown out in one embodiment.

In one embodiment, the one or more of the first and / or further recess (s) each have at least one shoulder on which they come in the axial direction from the front to the rear axial end face Recess begins or its depth increases, in one embodiment by at least 130%, in a further development by at least 400%, and which is therefore referred to as the front shoulder.

In one embodiment, the (respective) sealing element can advantageously be fixed in the axial direction, in particular positively, by the rear shoulder, in particular a displacement of the sealing element in the axial direction can be limited or prevented. In a further development, the (respective) sealing element advantageously (also) fixed against the axial direction, in particular positively, in particular a displacement of the sealing element against the axial direction can be limited or prevented.

According to one embodiment of the present invention, a blade arrangement has a blade described here, which is referred to as the first blade without loss of generality, and at least one further blade described here, which in a further development is structurally identical, which is referred to as a second blade without loss of generality and in one embodiment is or is arranged adjacent to the first blade in the circumferential direction or is provided for this purpose, in particular is set up, is or is used. In one embodiment, the first and / or second blades are (each) blades of a blade cluster or composite with a common (first or second) shroud and (each) a plurality of blade blades. In the case of such blade clusters that are adjacent in the circumferential direction, the present invention can be used with particular advantage, in particular for cooling.

According to one embodiment of the present invention, the vane arrangement has one or the one-part or multi-part (first) sealing element, which is partly in the first recess of the pressure-side or suction-side side surface of the first vane and partly in the first recess of this, in particular is received in the circumferential direction, adjacent or opposite, side surface of the second blade and in one embodiment thereby at least partially covers a gap between these two side surfaces, in particular closes, preferably seals, or is provided for this purpose, in particular designed, or is or is, in the area of the sealing element. is used.

According to one embodiment of the present invention, the vane arrangement has one or the one-part or multi-part further sealing element which, on the one hand, is partially in one or the further recess of the side surface of the first vane, which also has the first recess, and, on the other hand, partly in a or . the further recess of this side surface of the first blade, in particular in the circumferential direction, adjacent or opposite side surface of the second blade is received and in one embodiment also partially covers the gap between these two side surfaces, in particular closes it in the area of the further sealing element, preferably seals, or is provided for this purpose, in particular set up, is or is used.

As a result, in one embodiment, a free radial gap can advantageously be provided between the (first) sealing element at least partially accommodated in the first paragraph and the further sealing element at least partially accommodated in the further paragraph, through which coolant, in particular cooling air, from the shroud underside to the shroud upper side can flow and advantageously cool them.

Additionally or alternatively, according to one embodiment of the present invention, the vane arrangement has one or the one-part or multi-part further sealing element which, on the one hand, is partially in the first recess of the side surface of the first vane and, on the other hand, partly in the first recess of this side surface of the first vane, is received in particular in the circumferential direction, adjacent or opposite, side surface of the second blade and in one embodiment thereby also partially covers the gap between these two side surfaces, in particular closes, preferably seals, or is provided, in particular set up for this purpose, in the area of the further sealing element or is used.

As a result, in one embodiment, a free radial gap can advantageously be made available between the (first) sealing element at least partially accommodated in the first paragraph and the further sealing element at least partially accommodated in this first paragraph, through which coolant, in particular cooling air, from the underside of the shroud to the upper side can flow and advantageously cool them.

In one embodiment, the first sealing element and / or the one or more of the further sealing element (s) is / are strip-like and / or flat or kink-free in the axial direction. As a result, the manufacture, assembly, function, in particular sealing function, and / or reliability can be improved in one embodiment.

In one embodiment, between the two adjacent side surfaces of the first and second blades (axially) behind one or more (airfoil profile) trailing edge-side axial end face (s) of the first sealing element and / or (axially) behind one or more (airfoil profile) trailing edge-side axial end face ( n) of the or one or more of the further sealing element (s) (in each case), in particular (axially) adjoining this, a free radial gap is formed between the top and bottom of the two blades.

In one embodiment, this free radial gap or a rearmost of these free radial gaps extends as far as the rear axial end face of the shroud of the first and / or second blade. As a result, in one embodiment a particularly advantageous Cooling effect can be realized. In another embodiment, this free radial gap or a rearmost of these free radial gaps ends axially in front of the rear axial end face of the shroud of the first and / or second blade, in particular in that one or the further sealing element is arranged behind the sealing element.

In one embodiment, an axial, in particular maximum, minimum or mean, distance is at least one section of the or one or more of the trailing edge-side axial end face (s) of the first and second blades located in a gap or the gap between these adjacent side surfaces of the first and second blades / or the or one or more of the further sealing element / s, behind which one or the free radial gap or one of the free radial gaps is formed between the top and bottom of the two blades, from the front edge of the first and / or the second blade or its blade profile mentioned here (in each case) at least 40%, in one embodiment at least 50%, and / or at most 100%, in one embodiment at most 90%, of the axial profile depth of the first and / or second blade or their airfoil profile mentioned here.

As a result, in one embodiment, coolant, in particular cooling air, can advantageously flow from the underside of the shroud to the upper side of the shroud and cool the latter.

In one embodiment, the first and / or the or one or more of the further sealing element (s) through the rear shoulder and / or through the front shoulder of at least one of the two recesses in which it (each ) is partially received, in particular positively, axially fixed. As explained in the present case, this is understood to mean, in particular, a limitation of a displacement in or against the axial direction, and in a further development a prevention of a displacement in and against the axial direction.

According to one embodiment of the present invention, a turbomachine, in particular at least one compressor stage and / or preferably at least one turbine stage of a gas turbine, in one embodiment of an aircraft engine, has one or more of the blade arrangements described here.

In one embodiment, the turbomachine has at least one coolant plenum which is or will be delimited by the undersides of the (shrouds of the) first and second blades of the blade arrangement. In one embodiment, the coolant plenum, in particular through at least one compressor stage of the gas turbine, is supplied with coolant, preferably cooling air, which during operation at least temporarily from the coolant plenum through one or the free radial gap (s) that or which between the upper and bottom of the two blades is / are formed, flows to the top of the first and / or second blade. Correspondingly, the blade (arrangement) is particularly suitable for turbine stages of (aircraft engine) gas turbines, in particular also because a working fluid regularly has lower pressures in these in the rear region of the shrouds. However, the present invention is not limited to this.

According to one embodiment of the present invention, one or the one-part or multi-part first and / or one or more of the one-part or multi-part (n) further (s) sealing element (s), each partially in the (first or . further) recess of the one side surface of the shroud of the first blade and partially in the (first or further) recess of the side surface of the shroud of the second blade adjacent to this, or provided for this purpose, in particular set up, is or is used, (each) at least one axially closed on one side, in particular axially open to the rear elongated hole.

Additionally or alternatively, one or the one-part or multi-part first and / or one or more of the one-part or multi-part further sealing element (s), each partially in the (first or . further) recess of the one side surface of the shroud of the first blade and partially in the (first or further) recess of the side surface of the shroud of the second blade adjacent to this, or provided for this purpose, in particular set up, is or is used, (each) one or more (each) axially closed on both sides, in particular axially spaced or offset from one another, elongated holes and / or one or more, in particular axially spaced or offset from one another, through openings with a circular cross-section ("round hole").

In one embodiment, this elongated or round hole is or will be one or more of these elongated or round holes (each) at least partially in the gap between the side surface of the first blade and the side surface of the second blade adjacent to it arranged or provided for this purpose, in particular set up, or used and / or penetrates or penetrates (in each case) the sealing element.

As a result, in one embodiment, in particular in the case of one-piece sealing elements, free radial gaps can advantageously be made available, in particular positioned, through the coolant, in particular cooling air, from the underside of the shroud to Shroud upper side flow and this can advantageously cool.

Additionally or alternatively, in one embodiment, at least one axial end face, in particular on the rear edge side, of the first and / or one or more of the further sealing element (s) (each) has at least one axial shoulder, in particular an axial rear end face of a one-piece sealing element or an axial rear end face of at least part of a multi-part sealing element.

As a result, in one embodiment, a section of this axial end face can be advantageously positioned in one or the gap between the side face of the first vane and the side face of the second vane adjacent to it, in particular in the specified range of values.

A rear edge-side axial end face of a sealing element mentioned here is, in one embodiment, a rear axial end face of the one-piece sealing element or part of the multi-part sealing element or an (axially front) start of a through opening, in particular an elongated hole mentioned here or a round hole mentioned here, a section of this rear edge-side axial end surface in a gap between the side surface of the first blade and the side surface of the second blade adjacent to it, behind which a free radial gap is formed between the top and bottom of the two blades, corresponding to a section of this trailing edge-side axial end surface in this or within this Gap( s ) between the side surface of the first blade and the side surface of the second blade adjacent to it.

• - die Anordnung eines Abschnitts einer hinterkantenseitigen axialen Stirnfläche eines Dichtelements im Spalt zwischen den beiden benachbarten Seitenflächen der ersten und zweiten Schaufel in dem angegebenen axialen Abstand von der Vorderkante;
• - das wenigstens eine weitere Dichtelement;
• - das bzw. die Langlöcher und/oder Rundlöcher in dem bzw. einem oder mehreren der Dichtelemente; und/oder
• - der wenigstens eine Absatz wenigstens einer axialen Stirnfläche des bzw. eines oder mehrerer der Dichtelemente(s)

können besonders vorteilhaft miteinander kombiniert sein bzw. werden. Gleichwohl können sie auch jeweils einzeln realisiert sein bzw. werden.Two or more of the aforementioned aspects, in particular

• the arrangement of a section of a trailing edge-side axial end face of a sealing element in the gap between the two adjacent side faces of the first and second blades at the specified axial distance from the leading edge;
• - The at least one further sealing element;
• - The elongated hole or holes and / or round holes in the one or more of the sealing elements; and or
• - the at least one shoulder of at least one axial end face of the or one or more of the sealing elements ( s )

can be combined with one another particularly advantageously. Nevertheless, they can also be implemented individually.

As a result, in one embodiment, the cooling can be improved and / or the manufacturing expenditure can be reduced and / or the reliability can be increased.

• 1 eine Schaufelanordnung einer Turbomaschine mit zwei Schaufeln und einem Dichtelement nach einer Ausführung der vorliegenden Erfindung in einer Draufsicht;
• 2 einen Teil der Schaufelanordnung in einer Seitansicht;
• 3 eine Schaufelanordnung einer Turbomaschine mit zwei Schaufeln und einem Dichtelement nach einer weiteren Ausführung der vorliegenden Erfindung in 1 entsprechender Ansicht;
• 4 eine Schaufelanordnung einer Turbomaschine mit zwei Schaufeln und einem Dichtelement nach einer weiteren Ausführung der vorliegenden Erfindung in 1, 3 entsprechender Ansicht;
• 5 das Dichtelement der 4 in einer alleinigen Draufsicht;
• 6 ein Dichtelement einer Turbomaschine nach einer weiteren Ausführung der vorliegenden Erfindung in 5 entsprechender Ansicht;
• 7 ein Dichtelement einer Turbomaschine nach einer weiteren Ausführung der vorliegenden Erfindung in 5, 6 entsprechender Ansicht;
• 8 ein Dichtelement einer Turbomaschine nach einer weiteren Ausführung der vorliegenden Erfindung in 5, 6, 7 entsprechender Ansicht;
• 9 eine Schaufelanordnung einer Turbomaschine mit zwei Schaufeln und zwei Dichtelementen nach einer weiteren Ausführung der vorliegenden Erfindung in 1, 3, 4 entsprechender Ansicht; und
• 10 eine Schaufelanordnung einer Turbomaschine mit zwei Schaufeln und wenigstens einem Dichtelement nach einer weiteren Ausführung der vorliegenden Erfindung in 1, 3, 4, 9 entsprechender Ansicht.

Further advantageous developments of the present invention emerge from the subclaims and the following description of preferred embodiments. This shows, partly schematically:

• 1 a blade arrangement of a turbomachine with two blades and a sealing element according to an embodiment of the present invention in a plan view;
• 2 a part of the blade arrangement in a side view;
• 3 a blade arrangement of a turbomachine with two blades and a sealing element according to a further embodiment of the present invention in FIG 1 corresponding view;
• 4th a blade arrangement of a turbomachine with two blades and a sealing element according to a further embodiment of the present invention in FIG 1 , 3 corresponding view;
• 5 the sealing element of 4th in a sole plan view;
• 6th a sealing element of a turbomachine according to a further embodiment of the present invention in FIG 5 corresponding view;
• 7th a sealing element of a turbomachine according to a further embodiment of the present invention in FIG 5 , 6th corresponding view;
• 8th a sealing element of a turbomachine according to a further embodiment of the present invention in FIG 5 , 6th , 7th corresponding view;
• 9 a blade arrangement of a turbomachine with two blades and two sealing elements according to a further embodiment of the present invention in FIG 1 , 3 , 4th corresponding view; and
• 10 a blade arrangement of a turbomachine with two blades and at least one sealing element according to a further embodiment of the present invention in FIG 1 , 3 , 4th , 9 corresponding view.

1 shows a blade arrangement of a turbomachine with a first blade and one in the circumferential direction (vertical in 1 ) adjacent second blade according to an embodiment of the present invention in a radial plan view.

The first blade has a blade (profile) 100 with a leading edge 101 , a trailing edge 102 , a pressure side connecting these 103 and suction side 104 on, the second blade corresponding to a blade (profile) 200 with a leading edge 201 , a trailing edge 202 , a pressure side connecting these 203 and suction side 204 .

The first blade has a shroud 10 with an airfoil facing or in 1 Upper side visible in plan view 11 , one corresponding in 1 invisible underside facing away from the airfoil 12 (see. 2 ), a front axial face 13 and a rear axial end face 14th and a side surface on the print side 15th and a side surface on the suction side 16 on, respectively the top and bottom 11 , 12 and the two axial end faces 13 , 14th connect the second blade to a shroud accordingly 20th with an upper side facing the airfoil 21st , an underside facing away from the airfoil, a front axial end face 23 and a rear axial end face 24 and a side surface on the print side 25th and a side surface on the suction side 26th .

In each of these side faces 15th , 16 , 25th and 26th is a first recess in the form of an axial slot 30th , 40 (first shovel) or 50 , 60 (Second blade) arranged or formed, the or the one rear shoulder 31 , 41 , 51 or. 61 has, at which the recess ends and accordingly a recess-free section 4th (see. 2 ) of the side surface 15th , 16 , 25th or. 26th connects.

An axial distance x of this paragraph 31 , 41 , 51 or. 61 from the leading edge 101 or. 201 is between 40% and 100% of an axial profile depth c _ax , which is equal to the axial distance between the leading and trailing edge 101 , 102 or. 201 , 202 is.

The slots 30th , 40 , 50 and 60 each also have a front paragraph 32 , 42 , 52 or. 62 on, on which in the axial direction from the front to the rear axial end face coming the recess 30th , 40 , 50 or. 60 begins.

In the slots 30th and 50 a strip-like, in the axial direction kink-free or flat one-piece (first) sealing element in the form of a feather seal 1 is inserted so that it is partially in the slot 30th and partly in the slot 50 added and through the front paragraph 32 or. 52 and back paragraph 31 or. 51 is axially fixed and the gap between the two side surfaces 15th , 26th in the area of the sealing element 1 seals. In the same way, further sealing elements can be partially inserted in the slots 40 , 60 be recorded or fixed. The heels 31 , 32 , 51 and 52 each form axial stops.

During operation, cooling air can thus be drawn from a coolant plenum 3 , which is limited by the undersides of the first and second blades, by a free radial gap 2 to the top 11 , 21st the first and second blades flow.

Due to the straight rear axial face of the first sealing element 1 is also the axial distance x ' of the section of the trailing edge-side axial end face 1A this sealing element 1 in the gap s between the side faces 15th , 26th , behind which the free radial gap 2 is formed from the leading edge 101 or. 201 between 40% and 100% of the axial profile depth c _ax .

3 shows in 1 correspondingly, a blade arrangement of a turbomachine with two blades and a sealing element according to a further embodiment of the present invention. Features that correspond to one another are identified by the same reference symbols, so that reference is made to the above description and only differences are discussed below.

In the execution of the 3 are the rear paragraph 31 , 41 , 51 , 61 axially further from the leading edges 101 , 201 spaced as in the execution of the 1 . The rear axial face of the sealing element 1 but has axial shoulders 1B on with which the sealing element 1 form-fitting to the rear paragraph 31 , 51 supports.

In this way, the axial distance is also here x ' des in the gap s between the side faces 15th , 26th located section of the trailing edge-side axial end face 1A this sealing element 1 , behind which the free radial gap 2 is formed from the leading edge 101 or. 201 between 40% and 100% of the axial profile depth c _ax .

4th shows in 1 , 3 correspondingly a blade arrangement of a turbomachine with two blades and a sealing element according to a further embodiment of the present invention, 5 the sealing element in sole plan view. Features that correspond to one another are identified by the same reference symbols, so that reference is made to the above description and only differences are discussed below.

In the execution of the 4th , 5 are the rear paragraph 31 , 41 , 51 , 61 also axially further from the leading edges 101 , 201 spaced as in the execution of the 1 .

The sealing element 1 that as in the execution of the 1 has a straight rear axial end face, but has an elongated hole which is axially closed on both sides 1C on, its in the gap s between the side faces 15th , 26th located axially anterior or the beginning of the leading edge one in the gap s located section of a trailing edge-side axial end face 1A of the sealing element 1 forms, so that here too the axial distance x ' this in the gap s between the side faces 15th , 26th located section of this rear edge-side axial end face 1A this sealing element 1 , behind which a free radial gap 2 is formed from the leading edge 101 or. 201 between 40% and 100% of the axial profile depth c _ax amounts.

6th - 8th show in 5 corresponding view each one sealing element 1 a turbomachine according to a further embodiment of the present invention.

In contrast to the otherwise identical design of the 4th , 5 has the sealing element 1 the execution of the 6th several axially spaced round holes 1D , the sealing element 1 the execution of the 7th an axially closed slot on one side 1E and the sealing element 1 the execution of the 8th several axially spaced elongated holes 1F each with a free radial gap 2 between the top 11 , 21st and bottom 12 of the two blades.

9 shows in 1 , 3 and 4th correspondingly, a blade arrangement of a turbomachine with two blades and two sealing elements according to a further embodiment of the present invention. Features that correspond to one another are identified by the same reference symbols, so that reference is made to the above description and only differences are discussed below.

In the execution of the 9 has the blade arrangement in addition to the first sealing element 1 another one-part or multi-part sealing element 1' on, analogous to the partially in the first recess 30th or the recess 50 arranged first sealing element 1 partly in another recess 30 ' the side face 15th and partly in another recess 50 ' the side face 26th is arranged.

The axial distance is also here x ' des in the gap s between the side faces 15th , 26th located section of the trailing edge-side axial end face 1A of the first sealing element 1 , behind which a free radial gap 2 is formed from the leading edge 101 or. 201 between 40% and 100% of the axial profile depth c _ax .

10 shows in 1 , 3 , 4th and 9 correspondingly, a blade arrangement of a turbomachine with two blades and at least one sealing element according to a further embodiment of the present invention. Features that correspond to one another are identified by the same reference symbols, so that reference is made to the above description and only differences are discussed below.

In the execution of the 10 has a sealing element which is partially in the first recess 30th and partly in the first recess 50 is arranged two parts 1G , 1H a first one-piece sealing element is on or in these recesses 1G and another one-piece sealing element 1H arranged.

The front part or the first sealing element 1G has like the sealing element of the 7th an axially closed slot on one side 1E or like the sealing element of 3 paragraphs 1B to deal with this part 1G or the first sealing element 1G form-fitting to the rear part or the further sealing element 1H supports.

In addition, the rear part closes 1H the elongated hole closed axially on one side 1E to an axially closed slot on both sides 1C analogous to the execution of the 4th .

The axial distance is also here x ' des in the gap s between the side faces 15th , 26th located portion of the front of the two rear edge-side axial end faces of this multi-part sealing element or the rear edge-side axial end face of this one-piece first sealing element, behind which a free radial gap 2 is formed from the leading edge 101 or. 201 between 40% and 100% of the axial profile depth c _ax .

Although exemplary embodiments have been explained in the preceding description, it should be pointed out that a large number of modifications are possible.

In particular, in the explanations of 4th - 10 the sealing elements and / or elongated or round holes relative to the front edge 101 or. 201 also be positioned differently. In addition, several of the designs can also be combined, for example the sealing elements of 4-8 , 10 in the execution of the 9 be used.

It should also be pointed out that the exemplary designs are only examples that are not intended to restrict the scope of protection, the applications and the structure in any way. Rather, the preceding description provides the person skilled in the art with guidelines for the implementation of at least one exemplary embodiment, with various changes, in particular with regard to the function and arrangement of the components described, being able to be made without the scope of protection to leave, as it results from the claims and these equivalent combinations of features.

List of reference symbols

1; 1'

feather seal (sealing element)

1A

(Section of) the rear edge-side axial end face in gap s

1B

axial shoulder

1C

Long hole closed axially on both sides

1D

Round hole

1E

elongated hole closed axially on one side

1F

Long hole closed axially on both sides

1G

first one-piece sealing element

1H

another one-piece sealing element

2

free radial gap

3

Coolant plenum

4th

Recess-free side surface section

10/20

Shroud first / second blade

11/21

Top of first / second paddle

12

Bottom of first shovel

13/23

front axial end face first / second blade

14/24

rear axial end face first / second blade

15/25

Pressure side side surface first / second blade

16/26

Suction-side side surface first / second blade

100/200

Blade (profile) first / second blade

101/201

Leading edge of first / second blade

102/202

Trailing edge of first / second blade

103/203

Pressure side first / second blade

104/204

Suction side first / second blade

30, 40

Slot (first recess) first blade

50, 60

Slot (first recess) second blade

30 ', 40'

Slot (further recess) first blade

50 ', 60'

Slot (further recess) second blade

31, 41, 51, 61

rear heel

32, 42, 52, 62

front paragraph

c _ax

axial profile depth

s

gap

x; x '

axial distance

QUOTES INCLUDED IN THE DESCRIPTION

This list of the documents listed by the applicant was generated automatically and is included solely for the better information of the reader. The list is not part of the German patent or utility model application. The DPMA assumes no liability for any errors or omissions.

Patent literature cited

• US 5531457 A [0002, 0014]

Claims (13)

Blade for a turbomachine, in particular a compressor or turbine stage of a gas turbine, in particular an aircraft engine, the blade having at least one airfoil profile (100; 200), which has a leading edge (101; 201), a trailing edge (102; 202), and a connecting edge Has pressure side (103; 203) and suction side (104; 204), and has at least one shroud (10; 20) which has an upper side (11; 21) facing the airfoil, an underside (12) facing away from the airfoil, a front and a rear axial end face (13, 14; 23, 24) and a pressure side side surface (15; 25) which connects the top and bottom and the two axial end faces, and a suction side side surface (16; 26) which connects the top and bottom and connects the two axial end faces, with a first, in particular slot-like, recess (30, 40; 50, 60) for partially receiving at least one sealing element (1; 1G , 1H) is arranged, wherein the first recess has at least one rear shoulder (31, 41; 51, 61), at which a recess depth is reduced in an axial direction from the front to the rear axial end face and its axial distance (x) from the front edge in a range between 40%, in particular 50%, and 100%, in particular 90%, an axial profile depth (c _ax ) lies; and / or at least one further, in particular slot-like, recess (30 ', 40'; 50 ', 60') for partially receiving at least one further sealing element (1 ') is arranged in this side face. Blade according to the preceding claim, characterized in that coming in the axial direction from the front to the rear axial end face, the first recess ends at the shoulder or its recess depth is reduced to at most 75% at the shoulder. Shovel according to the preceding claim, characterized in that the side face has a section (4) without a recess adjoining the shoulder in the axial direction. Shovel according to one of the preceding claims, characterized in that the first recess has at least one front shoulder (32, 42; 52, 62) at which the first recess begins or extends in the axial direction from the front to the rear axial end face their recess depth increased. Sealing element (1; 1G, 1H) to be partially received in a first recess (30) of a pressure or suction side side surface (15) of a shroud (10) of a first blade, in particular according to one of the preceding claims or a blade arrangement according to one of the following claims , and partial accommodation in a first recess (50) of one of these adjacent side surfaces of a shroud (20) of a second blade, in particular the blade arrangement, the sealing element being strip-like and / or flat and / or at least one elongated hole closed axially on one or both sides ( 1C, 1E, 1F) and / or at least one round hole (1D) and / or at least one of its axial end faces has at least one axial shoulder (1B). A blade arrangement comprising: a first blade, in particular according to one of the preceding claims, which has at least one airfoil profile (100) which has a front edge (101), a rear edge (102), a pressure side (103) and suction side (104) connecting them, and has at least one shroud (10) which has a top side (11) facing the airfoil, an underside (12) facing away from the airfoil, a front and a rear axial end face (13, 14) and a side surface (15) on the pressure side, which the top and bottom and connects the two axial end faces, and has a suction-side side surface (16) which connects the top and bottom and the two axial end sides, with a first, in particular slot-like, recess (30, 40) for at least partial accommodation in at least one of these side surfaces a sealing element (1; 1G, 1H) is arranged, a second blade, in particular according to one of the preceding claims, the wen At least one airfoil profile (200), which has a leading edge (201), a rear edge (202), a pressure side (203) and suction side (204) connecting these, and at least one shroud (20) which has an upper side (21) facing the airfoil , an underside facing away from the airfoil, a front and a rear axial end face (23, 24) as well as a pressure side side surface (25) which connects the top and bottom side and the two axial end sides, and a suction side side surface (26) which has the upper - and the underside and the two axial end faces, with at least one, in particular slot-like, first recess (50, 60) for partially receiving the at least one sealing element (1; 1G, 1H) is arranged, and the at least one sealing element (1; 1G, 1H), in particular according to the preceding claim, which is partially in the first recess (30) of the pressure- or suction-side side surface (15) of the first blade and partially in the first Recess (50) of this adjacent side surface (26) of the second blade is received. Blade arrangement according to the preceding claim, characterized in that a free radial gap (2) is formed between the top and bottom of the two blades between the two adjacent side surfaces of the first and second blades behind at least one rear-edge axial end surface of this sealing element. Blade arrangement according to the preceding claim, characterized in that an axial distance (x ') of at least a portion of a trailing edge-side axial end face (1A) of this sealing element in a gap (s) between the side surface (15) of the first blade and the side surface (15) adjacent to it. 26) of the second blade, behind which a free radial gap (2) is formed between the top and bottom of the two blades, from the front edge (101; 201) of the first and / or second blade in a range between 40%, in particular 50 %, and 100%, in particular 90%, of their axial profile depth (c _ax ). Blade arrangement according to one of the preceding claims, characterized in that the at least one sealing element is axially fixed by the rear and / or front shoulder of at least one of the two recesses. Blade arrangement according to one of the preceding claims, characterized by at least one further sealing element (1 '; 1H), in particular according to Claim 5 which is partly in the first recess (30) of the side surface (15) of the first blade and partly in the first recess (50) of the side surface (26) of the second blade adjacent to it or partly in a further recess (30 ') of this side surface ( 15) of the first blade and partially in a further recess (50 ') of the side surface (26) of the second blade adjacent to it. Turbomachine, in particular gas turbine, in particular aircraft engine gas turbine, with at least one blade arrangement according to one of the preceding claims. Turbomachine according to the preceding claim, characterized by at least one coolant plenum (3) which is delimited by the undersides of the first and second blades of the blade arrangement. Method for operating a turbo machine according to the preceding claim, characterized in that at least temporarily coolant flows from the coolant plenum (3) through at least one free radial gap (2) to the upper side (11; 21) of the first and / or second blade, which flows between the two adjacent side surfaces and is formed between the top and bottom of the two blades.

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