EP3128132B1 - Turbo engine guide blade ring element - Google Patents

Description

The present invention relates to a guide vane ring element for a turbomachine, in particular a gas turbine, a guide element with the guide vane ring element, a turbomachine, in particular a gas turbine, with the guide element and a method for producing the guide vane ring element.

From the US 2011/0293406 A1 is a guide vane ring member with holes for partially receiving flanges rotatable vanes known. In a peripheral region of a bore, which is swept by a bore-side end face of an airfoil of the vane, the edge of the bore due to the expansion of the airfoil on a slight chamfer.

An object of an embodiment of the present invention is to improve a turbomachine, in particular a gas turbine.

This object is achieved by a guide blade ring element having the features of claim 1. Claims 10, 12 and 13 provide protection for a guide grid element with a guide blade ring element described here, a turbomachine with a guide grid element described here or a method for producing a guide blade ring element described here. Advantageous embodiments of the invention are the subject of the dependent claims.

According to one aspect of the present invention, a turbomachine, in particular a gas turbine, in particular an aircraft engine gas turbine, in particular a compressor of the gas turbine, has one or more adjustable guide grid elements.

In one embodiment, a guide grid element can be circular or ring segment-like, so that a plurality of guide grid elements or segments together form a (closed) guide grid ring, in particular a guide grid, the turbomachine, in particular a stage, in particular compressor stage, of the gas turbine or provided for this purpose or are formed. Similarly, a guide grid element in another embodiment (full) circular or ring-like design and in a development of a (closed) Leitgitterring, In particular, a guide grid, the turbomachine, in particular a stage, in particular compressor stage, the gas turbine form or provided for this purpose or be formed.

A baffle element in one embodiment has one or more vane ring elements and one or more adjustable vanes.

A Leitschaufelringelement may be circular or ring segment-like in one embodiment, so that a plurality of Leitschaufelringelemente or segments together form a (closed) Leitschaufelring the turbomachine, especially one or the stage, in particular compressor stage, the gas turbine or provided for this purpose or are formed. Similarly, a guide vane ring element in another embodiment (full) circular or ring-like design and in a development a (closed) Leitschaufelring the turbomachine, in particular one or the stage, in particular compressor stage, the gas turbine form or provided for this purpose or trained his. Ring segments and solid rings are referred to herein for compact presentation together as elements.

In one embodiment, the vane ring element may be disposed radially inward or radially outward of the vanes, or may be a (radially) inner or (radially) outer vane ring element.

In one embodiment, the guide vanes each have an airfoil and a, in particular cylindrical and / or cone-like, flange, which is accommodated rotatably completely or partially in a bore of the guide vane ring element or one of the vane ring elements.

The flange may be arranged on the front side or on a radial end of the guide vane. In other words, the guide vane can terminate in the radial direction with the flange or end in this.

In another embodiment, the guide vane on the side of the flange radially opposite the airfoil may have a, in particular cylindrical and / or cone-like, extension or shoulder. Its maximum diameter in one embodiment is at most 90%, in particular at most 80%, and / or at least 10%, in particular at least 20%, of a minimum diameter of the flange. Additionally or alternatively, the radial height of the extension or heel in one embodiment is at least 10%, in particular at least 20%, and / or at most 200%, in particular at most 100%, one, in particular minimum, radial height of the flange.

In one embodiment, the flange connects radially to the airfoil of the vane, in particular in a fillet.

In particular, the flange may be a (rotary) plate or a (rotary) pin of the rotatable vane.

In one embodiment, it has the shape of a straight or obliquely cut cylinder or cone. In one embodiment, it has a chamfer or a radius on a side radially opposite the airfoil.

Accordingly, one or the guide vane ring element for one or the turbomachine, in particular gas turbine, in particular a Leitschaufelringelement one or the turbomachine, according to one aspect of the present invention, one or more holes, in each of which a flange of a rotatable or adjustable vane rotatably completely or partially (radially) is received or which are provided or set up for this purpose.

In one embodiment, the bores are, at least substantially, cylindrical and / or extend, in particular also or at least substantially, in the radial direction of the turbomachine or perpendicular to its main or rotational axis.

The bores each have a blade-blade-side edge or the edge of the blades of the guide blades, in which they merge into a blade-blade-side lateral surface of the guide blade ring element. In other words, an edge of a bore limits or defines its opening to or in the lateral surface of the guide blade ring element.

According to one aspect of the present invention, the edge of one or more of the bores (respectively) is formed convexly along the edge at least in a first circumferential region. In other words, the hole points in one or more (Transverse) along a Bohrungslängs-- or Leitschelt rotational axis in each case a convex or curved toward the vane edge.

In this way, in one embodiment, in particular in comparison to a chamfer, advantageously a leakage between the guide blade ring element and the guide blade, in particular a bore-side or the bore-facing end face of its blade can be reduced. Additionally or alternatively, in one embodiment, advantageously an extension of the edge and thus a disturbance of the flow can be reduced.

In one embodiment, one or the bore-side end face of an airfoil of a vane in a neutral or middle position of the adjustable vane is radially opposite the first peripheral region, in particular its center in the circumferential direction of the edge. The first circumferential region extends in one embodiment over at least 2%, in particular at least 5%, and / or at most 50%, in particular at most 25%, of a length of the edge in the circumferential direction.

The edge in the first peripheral region has a radius. In other words, the bore in a first peripheral region of its edge in, in particular all, (transverse) sections along one or the Bohrungslängs- or Leitscheltrehrehachse each at its (blade edge side) edge, in particular curved toward the guide vane or convex, rounding on or goes in a radius in the blade-leaf-side lateral surface of the Leitschaufelringelements over.

In particular, a radius can be advantageous in terms of production and / or flow technology, in particular leakage technology.

In one embodiment, the radius in the first peripheral region is constant or changes by a maximum of 1%. Such a constant radius can be particularly advantageous in terms of manufacturing technology, particularly advantageous; in particular, it can be produced by a form milling cutter.

In another embodiment, the radius in the first peripheral region varies along the edge, in particular by at least 10%. Such a varying radius can in particular be particularly advantageous in terms of flow, it can be prepared in particular by a flank and / or end mill and / or line by line or be.

In a further development, the radius increases along the edge in a first subregion of the first peripheral region and along the edge in an adjoining, in particular shorter, second subregion of the first peripheral region. The first and second subareas may together form the first peripheral area. Such an asymmetrically varying radius can be particularly advantageous in terms of flow, in particular, it can be produced by a flank cutter and / or face milling cutter.

In one embodiment, the edge in a second peripheral region along the edge of a, in particular pointed or blunt edge, a chamfer or a, in particular constant, radius. The first and second peripheral regions may together form the edge. Likewise, in addition to the first and second peripheral regions, the rim may have one or two further peripheral regions in which, in one embodiment, it may have an edge or chamfer. Correspondingly, in one embodiment, the second circumferential region extends over at least 50%, in particular at least 75%, of one or the length of the edge in the circumferential direction.

By means of a second circumferential region having a radius, in one embodiment, in particular, the production and / or flow of the first peripheral region can be improved.

In a development, one or the maximum radius in the second circumferential region is smaller than one, in particular maximum and / or minimum, radius in the first peripheral region, in one embodiment the maximum radius in the second peripheral region is at most 50%, in particular at most 25%. , one, in particular maximum and / or minimum, radius' in the first peripheral region.

In one embodiment, one, in particular maximum or minimum, radius in the first peripheral region is at least 1%, in particular at least 2%, in particular at least 5%, in particular at least 10%, and / or at most 50%, in particular at most 30%, in particular at most 10 %, of a radius. Additionally or alternatively, in one embodiment, one or more, in particular maximum (r) or minimum (r), radius in the first circumferential region at least 1%, in particular at least 2%, in particular at least 5%, in particular at least 10%, and / or at most 50%, in particular at most 30%, in particular at most 10%, of a radial depth of the bore at this circumferential position, in particular of the blade surface side surface the vane ring element up to a bottom or shoulder of the bore.

In one embodiment, the edge is or at least in the first peripheral region, in a development in the second peripheral region, machined, in particular with a form cutter, edited, in particular produced.

The bore is in one embodiment a through hole, in another embodiment, a one-sided closed or blind hole. It may be formed without a shoulder in an embodiment in the radial direction or have one or more paragraphs.

The flange of a vane contacted in one embodiment, a bottom or shoulder of him at least partially receiving bore or is based thereon radially.

The term "radial" refers in particular to the turbomachine. Accordingly, the radial direction is perpendicular to a main or rotational axis of the turbomachine.

Fig. 1

eine perspektivische Ansicht eines Teils eines Leitschaufelringelements einer Turbomaschine nach einer Ausführung der vorliegenden Erfindung;

Fig. 2

einen Schnitt durch das Leitschaufelringelement mit einer Leitschaufel längs einer Drehachse der Leitschaufel in einer Neutralstellung der Leitschaufel; und

Fig. 3

einen Fig. 2 entsprechenden Schnitt während eines Herstellens des Leitschaufelringelements nach einer Ausführung der vorliegenden Erfindung.

Further advantageous developments of the present invention will become apparent from the dependent claims and the following description of preferred embodiments. This shows, partially schematized:

Fig. 1

a perspective view of a portion of a vane ring element of a turbomachine according to an embodiment of the present invention;

Fig. 2

a section through the vane ring element with a vane along an axis of rotation of the vane in a neutral position of the vane; and

Fig. 3

one Fig. 2 corresponding section during manufacture of the vane ring element according to an embodiment of the present invention.

Fig. 1 shows a perspective view of a portion of a radially inner vane ring element 10 of a turbomachine according to an embodiment of the present invention, Fig. 2 a section through the vane ring element with a vane 20 along a rotation axis of the vane (vertically in Fig. 2 ) in a neutral position of the vane.

The vane has a flange 21 rotatably received in a bore 30 of the vane ring element.

The bore 30 has a blade-blade-side edge in which it merges into a blade-blade-side lateral surface 11 of the guide blade ring element. This edge consists of a first peripheral region (31A, 31B) and a second peripheral region 32.

In the in Fig. 2 shown neutral or middle position of the adjustable guide vane 20 is a bore side (in Fig. 2 Lower) end face of a blade of the vane of the center of the first peripheral portion 31A, 31B in the circumferential direction of the edge radially opposite.

The edge points, as in particular on average the Fig. 2 recognizable, in the first peripheral region 31A, 31B has a radius R.

In the exemplary embodiment, the radius decreases in a first partial region 31A of the first circumferential region along the edge and in a subsequent shorter second partial region 31B of the first peripheral region along the edge, wherein the first and second partial regions together form the first peripheral region 31A, 31B.

In a modification, the average of the Fig. 2 appears identical, the radius R in the first peripheral region 31A, 31B is constant.

In the exemplary embodiment, the edge in the second peripheral region 32 has a constant radius along the edge, which is significantly smaller than a maximum radius in the first peripheral region 31A, 31B and therefore in the schematic section of FIG Fig. 2 is not recognizable. In a modification, the second peripheral region can also have a pointed or blunt edge or a chamfer.

The first peripheral portion 31A, 31B is machined by means of a form cutter 40 as shown in FIG Fig. 3 is shown.

Although exemplary embodiments have been explained in the foregoing description, it should be understood that a variety of modifications are possible.

In particular, in the exemplary embodiment, the guide vane 20 on the radial side of the flange 21 opposite the airfoil (and thus in FIG Fig. 2 ) on a cylindrical extension or paragraph. In a modification, not shown, the guide vane 20 may terminate in the radial direction with the flange 21 and end in this.

The bore 30 is in the embodiment of a through hole, which has a paragraph in the radial direction, on which the flange 21 is radially supported. In a modification, not shown, the bore 30 may also be a blind hole.

Both modifications can be combined, so that the then end flange is supported radially on the bottom of the blind hole.

It should also be noted that the exemplary embodiments are merely examples that are not intended to limit the scope, applications and construction in any way. Rather, the expert is given by the preceding description, a guide 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, can be made without departing from the scope, as it turns out according to the claims and these equivalent combinations of features.

LIST OF REFERENCE NUMBERS

10

Leitschaufelringelement

11

lateral surface

20

vane

21

flange

30

drilling

31A

first subregion of the first peripheral region

31B

second subregion of the first peripheral region

32

second peripheral area

40

form cutters

R

radius

Claims (14)

1. Guide vane ring element (10) for a turbomachine, in particular a gas turbine, comprising at least one bore (30) for receiving a flange (21) of a rotatable guide vane (20) at least in part, characterized in that
   an airfoil-side rim of the bore is convex in a first circumferential region (31A, 31B) along the rim.
2. Guide vane ring element (10) according to claim 1, characterized in that the rim has a radius (R) in the first circumferential region (31A, 31B).
3. Guide vane ring element (10) according to claim 2, characterized in that the radius (R) in the first circumferential region (31A, 31B) is constant.
4. Guide vane ring element (10) according to claim 2, characterized in that the radius (R) in the first circumferential region (31A, 31B) varies along the rim.
5. Guide vane ring element (10) according to claim 4, characterized in that the radius (R) in a first portion (31A) of the first circumferential region increases along the rim and in an adjacent, in particular shorter, second portion (31B) of the first circumferential region, decreases along the rim.
6. Guide vane ring element (10) according to any of the preceding claims, characterized in that a radius (R) in the first circumferential region (31A, 31B) is at least 1% and/or at most 50% of a radius and/or of a radial depth of the bore (30).
7. Guide vane ring element (10) according to any of the preceding claims, characterized in that the rim has an in particular sharp or blunt edge, a chamfer or an in particular constant radius in a second circumferential region (32) along the rim.
8. Guide vane ring element (10) according to claim 7, characterized in that the maximum radius in the second circumferential region (32) is smaller than an in particular maximum and/or minimum radius (R) in the first circumferential region (31A, 31B).
9. Guide vane ring element (10) according to any of the preceding claims, characterized in that the rim has been machined, in particular by means of a forming cutter, at least in the first circumferential region (31A, 31B).
10. Guide vane ring element (10) according to any of the preceding claims, characterized in that the convex rim is formed by a ruled surface.
11. Guide baffle element comprising at least one guide vane ring element (10) according to any of the preceding claims and at least one adjustable guide vane (20) comprising a flange (21) which is rotatably received in one of the bores (30) of the guide vane ring element at least in part.
12. Guide baffle element according to claim 11, characterized in that a bore-side end face of an airfoil of the guide vane (20) in a neutral position of the adjustable guide vane is radially opposite the first circumferential region (31A, 31B), in particular the center thereof.
13. Turbomachine, in particular a gas turbine, comprising at least one guide baffle element according to either of the preceding claims 11 or 12.
14. Method for producing a guide vane ring element (10) according to any claims 1 to 10, characterized in that the rim is machined, in particular by means of a forming cutter (40), at least in the first circumferential region (31A, 31B).

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