EP3495629A1 - Turboengine flow channel - Google Patents

Abstract

The present invention relates to a flow channel for a turbomachine, in particular a gas turbine, with a plurality of ribs (11-23), which are arranged between a radially inner circumferential surface (2) and a radially outer circumferential surface (1) of the flow channel and distributed in the circumferential direction wherein a first one (11) of the ribs has a first rib thickness (d) and a first rib length (l) and a second (12) of the ribs has a second rib thickness (d) and a second rib length (l), the second rib length being smaller as the first rib length and / or the second rib thickness is smaller than the first rib thickness, and wherein in the first rib a first inner structure (31) having a first structure thickness (d) and in the second rib a second inner structure (32) is arranged, which has a second structure thickness (d), which is smaller than the first structure thickness; and / or a distance (T) in the circumferential direction between the first and the adjacent second rib and a distance (T) in the circumferential direction between at least two adjacent (12, 13) of the ribs differ from each other and at least one of these ribs a non-deflecting outer profile (A , A) and / or in an inner structure (32) is arranged.

Description

The present invention relates to a flow, in particular transition channel for a turbomachine, in particular a gas turbine, a turbomachine, in particular gas turbine, with the flow or transition channel and an aircraft engine with the gas turbine.

From the EP 2 669 474 A1 is a transition channel with support ribs and flow splitter vanes with a solid cross section and an outer profile for deflecting a flow known having different distances in the circumferential direction and different chord lengths.

From the US 3,704,075 is a flow channel between two rotors is known in the circumferentially uniformly distributed vanes and support ribs are arranged with lines.

An object of an embodiment of the present invention is to improve a turbomachine.

This object is achieved by a flow channel having the features of claim 1. Claims 8, 9 provide a turbomachine, in particular gas turbine, with one or more flow channels described herein or an aircraft engine with such a gas turbine under protection, advantageous embodiments of the invention are the subject of the dependent claims.

According to one embodiment of the present invention, a flow channel for a, in particular a flow channel of a turbomachine, in particular axial (n) turbomachinery, in particular gas turbine, in particular an aircraft engine, a plurality of ribs, which between a radially inner circumferential surface and a radially outer circumferential surface arranged the flow channel, in one embodiment detachable or non-detachable, in particular cohesively, with the inner and / or outer Coated surface or integrally formed, and / or in a circumferential direction, in particular at least partially adjacent to each other or in the axial direction at least partially overlapping, distributed, wherein a first of the ribs a first, in particular maximum, minimum or average, rib thickness, in particular in the circumferential direction (measured ), and a first, in particular maximum, minimum or average, rib length, in particular chord length and / or in the axial direction (measured), and a second of the ribs a second, in particular maximum, minimum or average, rib thickness, in particular in the circumferential direction (measured), and a second, in particular maximum, minimum or average, rib length, in particular chord length and / or in the axial direction (measured), having.

In one embodiment, the axial direction is parallel to a rotational, in particular (main) machine axis, the turbomachine, and the circumferential direction is in particular a direction of rotation about this axis. A radial direction is in an embodiment perpendicular to the axial and circumferential directions.

According to one embodiment of the present invention, this second rib length is smaller than this first rib length, in one embodiment at least 1%, in particular at least 5%, in one embodiment at least 15%, and / or at most 200%, in particular at most 100 %, in one embodiment at most 50%, of the first or second rib length. Additionally or alternatively, according to an embodiment of the present invention, this second rib thickness is smaller than this first rib thickness, in one embodiment at least 1%, in particular at least 5%, in one embodiment at least 15%, and / or at most 200%, in particular by not more than 100%, in one embodiment by more than 50%, of the first or second rib thickness.

According to one embodiment of the present invention, in the first rib a first internal structure having a first, in particular maximum, minimum or average, structural thickness, in particular in the circumferential or axial direction (measured), and in the second rib, a second internal structure, the a second, in particular maximum, minimum or average structural thickness, in particular in the circumferential or axial direction (measured), which is smaller than the first structural thickness, in one embodiment by at least 1%, in particular by at least 5%, in one embodiment by at least 15%, and / or by at most 200%, in particular by at most 100%, in an embodiment by at most 50%, of the first or second structural thickness.

In other words, according to an embodiment of the present invention, at least one (first) rib in which a thicker inner structure is arranged is thicker and / or longer than at least one (second) rib in which a thinner internal structure is arranged or is.

As a result, in one embodiment, a weight and / or efficiency can be improved.

In one embodiment, for one or more pairs A, B of the plurality of fins (each), a deviation | (d _A / I _A ) - (d _B / I _B ) | between a ratio d _A / l _{A of} a, in particular maximum, minimum or average, rib thickness d _A , in particular in the circumferential direction (measured), divided by one, in particular maximum, minimum or average, rib length l _A , in particular chord length and / or in the axial direction (measured), a rib A of these two ribs (of the respective pair) and a ratio d _B / l _B one, in particular maximum, minimum or average, rib thickness d _B , in particular in the circumferential direction (measured), divided by one, in particular maximum , minimum or average, rib length l _B , in particular chord length and / or in the axial direction (measured), the other rib B of these two ribs (the respective pair each) at most 15%, in particular at most 10%, in one embodiment at most 5%, in particular at most 1%, of the smaller or larger of these two ratios, wherein in this one rib A (each) an internal structure with one, in particular maxim alen, minimum or average, structure thickness, in particular in the circumferential or axial direction (measured), which, in particular by at least 1% and / or at most 200%, smaller as an, in particular maximum, minimum or average, structural thickness, in particular in the circumferential or axial direction (measured), an inner structure which is arranged in this other rib B, wherein in one embodiment, the rib length l _{A of} this one rib A, in particular at least 1%, in particular by at least 5%, in an embodiment by at least 15%, and / or by at most 200%, in particular by at most 100%, in an embodiment by at most 50%, the larger or smaller of the two rib lengths l _A , l _B smaller than the rib length l _{B of} this other rib B of the two ribs (of the respective pair) and / or the rib thickness d _{A of} this one rib A, in particular by at least 1%, in particular by at least 5%, in an embodiment by at least 15 %, and / or by at most 200%, in particular by at most 100%, in one embodiment by at most 50%, the larger or smaller of the two rib thicknesses d _A , d _B smaller than the rib thickness d _{B of} the other n B of the two ribs (of the respective pair) is.

In particular, the one and other ribs of a pair may be the aforementioned first and second ribs. The one and other ribs of one or more pairs may be adjacent in one embodiment (each in the circumferential direction). Similarly, in one embodiment between the one and other ribs of one or more pairs (each in the circumferential direction) one or more further ribs without internal structure and / or with at least substantially the same rib thickness and length as the one or the other rib may be arranged.

In other words, according to an embodiment of the present invention, for two or more of the ribs having different thickness inner structures, at least substantially, the same rib thickness / aspect ratio d / 1 is present.

As a result, in one embodiment, a weight and / or efficiency (further) can be improved.

In addition or as an alternative to the above-described aspect of different rib thicknesses and / or lengths, in particular with at least substantially equal rib thickness / length ratio d / l, differing inner structures differ or deviate according to an embodiment of the present invention, a distance T ₁₂ in the circumferential direction between the first and the second circumferential ribs (circumferentially) and a circumferential spacing Tc between at least two (circumferentially) adjacent ones of the ribs, in particular the distance T ₁₂ between the first and second ribs and the distance T ₁₃ between the first ribs and a third rib disposed on an opposite side of the first rib from the second rib, the distance T ₁₂ between the first and second ribs, and a distance T ₂₃ between the second and third ribs located on an opposite side of the first rib the second rib is arranged, and / o the distance T ₁₂ between the first and second ribs and distance T ₃₄ between a third and circumferentially adjacent fourth ribs different from the first and second ribs (apart from each other), wherein in one embodiment at least one these ribs, in particular the first, second, third and / or fourth rib, (each) has a non-deflecting outer profile and additionally or alternatively in at least one of these ribs, in particular the first, second, third and / or fourth rib, (respectively) one Inner structure is arranged, in particular in the first rib, the first inner structure and / or in the second rib, the second inner structure.

In one embodiment, these two distances differ or deviate by at least 1%, in particular by at least 5%, in one embodiment by at least 15%, and / or by at most 200%, in particular by at most 100%, in one embodiment by a maximum of 50%. , the larger or smaller of the two distances (from each other).

In other words, it is proposed according to this aspect, ribs having at least partially different rib lengths and / or thicknesses, one or have a plurality of each inner structures and / or non-deflecting outer profiles to distribute unevenly in the circumferential direction.

As a result, in one embodiment, a frequency or resonance behavior of the flow channel can be improved.

As already mentioned, these two aspects of different rib thicknesses and / or lengths, in particular with at least substantially equal rib thickness / length ratio d / l, for differently thick internal structures on the one hand and an uneven circumferential distribution of ribs with at least partially different rib lengths and / or thickness, which at least partially have internal structures and / or non-deflecting outer profiles, on the other hand be realized independently of each other, but in one embodiment, they are advantageously combined with each other. In other words, in one embodiment or combination of both aspects, the plurality of ribs have ribs, two or more of which have different thickness inner structures as well as different rib thicknesses and / or lengths, in particular with at least substantially the same rib thickness / length ratio in addition, these and / or other ribs of the plurality are distributed unevenly in the circumferential distribution.

As a result, in one embodiment, a frequency or resonance behavior and / or efficiency of the flow channel can be (further) improved.

In one embodiment, the symmetry of the flow channel in a region between the inner and outer circumferential surfaces due to the respective circumferential positions and / or the respective dimensions of each of the plurality of ribs has a count n, where n ≦ 8, n ≦ 7, n ≦ 6, n ≦ 5, n ≦ 4, n ≦ 3, n ≦ 2, n ≦ 8, n ≦ 4, n ≦ 2 and / or n = 1. For this purpose, only the circumferential positions and / or dimensions of the plurality of ribs are considered, but not a symmetry of any contoured radially inner and outer gas channel walls. A count of n means that a rotated fin arrangement for the first time rotates through 360 ° / n the rotational, in particular (main) machine axis, the turbomachine, again coincides with the unrotated rib arrangement with respect to circumferential positions of the ribs or with respect to circumferential positions and dimensions of the ribs. That is, there are exactly n congruent rib arrangements with respect to rib spacing and / or rib formation during a rotation through 360 °. This can enable a particularly efficient material-saving arrangement, in which the overall arrangement of the ribs with respect to the individual circumferential positions, the individual rib spacings and / or the respective dimensions of the individual ribs, in particular taking into account aerodynamic aspects, are adapted especially to the periphery.

In one embodiment, the first rib and / or the second rib, in particular the first rib, in which the first inner structure is arranged and / or the second rib, in which the second inner structure is arranged, whose structure thickness is smaller than the first structure thickness, (Each) a non-deflecting outer profile, in particular in addition to or without deviating distance (s) in the circumferential direction or a non-uniform circumferential distribution (s) of the plurality of ribs.

A non-deflecting outer profile is configured in one embodiment such that it does not change, at least substantially, a flow of a working fluid, in particular gas, in or through the flow channel, in particular such that a direction of outflow from a downstream trailing edge of the outer profile deviates by a maximum of 5 °, in particular at most 1 °, from a direction of, in particular purely axial, flow to an upstream leading edge of the outer profile and / or the axial direction. In one embodiment, an angle of incidence of the outer profile and / or an angle between a chord of the outer profile and the axial direction (respectively) is at most 5 °, in particular at most 1 °. Additionally or alternatively, in one embodiment, a profile curvature or maximum deviation of a skeleton line from a chord of the outer profile is at most 0.01, in particular at most 0.005. In one embodiment is a non-deflecting Outer profile along its axial longitudinal axis, at least substantially, mirror-symmetrical.

As a result, in one embodiment, a frequency or resonance behavior and / or efficiency of the flow channel can be (further) improved.

One or more of the inner structures, in particular therefore the first and / or second inner structure and / or the inner structure, in one or the other rib of at least one of the pairs with diverging distances in the circumferential direction and / or at least substantially the same rib thickness / length ratio one or more support strut (s) and / or one or more passage (s) provided or adapted for the passage of gas and / or liquid, or may have (in each case), in particular his. A through-passage for the passage of gas and / or liquid in one embodiment has an interface, in particular a connection for introducing and / or discharging gas and / or liquid.

In one embodiment, various of the inner structures may have different types of through passages, in particular, at least one of the inner structures a support strut and at least one other of the inner structures a passage for passage of a gas or a liquid, at least one of the inner structures a passage for passage of a Gas and at least one other of the internal structures, a passage for passage of a liquid and / or at least one of the internal structures, a passage for passage of a gas or a liquid and at least one other of the internal structures, a passage for passage of another gas or other liquid.

By supporting struts, in one embodiment, the radially inner and outer circumferential surface of the flow channel can be advantageously supported against each other by Through passages lubricant, in particular oil, coolant, in particular air, and / or other resources advantageously, in particular on short distances, are performed.

One or more of the inner structures, in particular therefore the first and / or second inner structure and / or the inner structure, in one or the other rib of at least one of the pairs with diverging distances in the circumferential direction and / or at least substantially the same rib thickness / length ratio is (are) completely or partially integrally with the (respective) rib in which it is or can be prepared. This applies in particular to (integrally manufactured or trained) passage passages.

Equally, one or more of the inner structures, in particular therefore the first and / or second inner structure and / or the inner structure, in the one or the other rib of at least one of the pairs with diverging distances in the circumferential direction and / or at least substantially the same Rib thickness / length ratio is arranged to be made (in each case) completely or partially separately from the (respective) rib in which it is or are arranged. This applies in particular to (separately produced or trained) support struts. Likewise, in addition or alternatively, through-passages may also be manufactured or formed separately, in particular having or being pipes, conduits or the like.

In one embodiment, one or more groups of (in each case below) identical ribs of the plurality of ribs arranged between the inner and outer lateral surface are or are distributed uniformly in the circumferential direction (in each case below one another) and / or one or more groups of (in each case under identical) (other) ribs of the plurality in the circumferential direction (each below) unevenly distributed. In one embodiment, a pitch between fins of a group of evenly spaced fins varies by at most 2%, especially at most 1%. additionally or alternatively, in one embodiment, a pitch between ribs of a group of unevenly distributed ribs varies by at least 5%, more preferably at least 10%, with a pitch in the usual manner, in particular minimum, maximum or average, circumferential spacing between successive structurally identical ribs of the respective group is.

In one embodiment, at least one support strut and / or at least one group of unevenly distributed ribs in the ribs of at least one group of uniformly distributed ribs in each case at least one through-passage for the passage of gas and / or liquid.

As a result, in one embodiment, the frequency distribution or resonance behavior and / or efficiency of the flow channel and at the same time the even distribution of a weight and / or force distribution can be improved (further) advantageously by the uneven distribution.

In one embodiment, the flow channel is a so-called transitional channel, which in an embodiment connects an upstream flow cross section of the turbomachine with a radially displaced downstream flow cross section of the turbomachine or is provided or set up or used for this purpose. In one embodiment, the flow or transition channel connects two compressors, in particular a high and a medium or low pressure compressor or a medium and a low pressure compressor, or two turbines, in particular a high and a medium or low pressure turbine or a middle and a low-pressure turbine, the turbomachine or is provided or set up for this purpose or is used for this purpose.

In one embodiment, the turbomachine is an axial (flow-through turbomachine, in particular a gas turbine, in particular an aircraft engine.

This represents particularly advantageous applications of a flow channel according to the invention.

Fig. 1

einen Querschnitt eines Übergangskanals nach einer Ausführung der vorliegenden Erfindung;

Fig. 2

einen Medianschnitt längs der Linie II-II in Fig. 1; und

Fig. 3

einen weiteren Medianschnitt längs der Linie III-III in Fig. 1.

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 cross section of a transition channel according to an embodiment of the present invention;

Fig. 2

a median section along the line II-II in Fig. 1 ; and

Fig. 3

another median section along the line III-III in Fig. 1 ,

Fig. 1 shows a cross section of a transition channel according to an embodiment of the present invention with a radially outer circumferential surface 1 and a radially inner circumferential surface 2 and a plurality of ribs 11-23 with a first rib 11, a second rib 12, a third rib 13, a fourth rib 14 etc. In the median sections of the Fig. 2, 3rd is in each case a cross section of the illustrated rib screwed in, so that in Fig. 2 the outer profile A _{11 of} the first rib 11 and in Fig. 3 the outer profile A _{12 of} the second rib 12 can be seen.

The first rib 11 has a first rib thickness d ₁₁ and a first rib length ₁₁ (see FIG. Fig. 2 ), the second rib 12 has a second rib thickness d ₁₂ smaller than the first rib thickness d ₁₁ , and a second rib length l ₁₂ smaller than the first rib length ₁₁ .

In the first rib 11, a first internal structure in the form of an air supply 31, which has a first structure thickness d ₃₁ , and in the second rib 12 a second internal structure in the form of a support strut 32, which has a second structure thickness d ₃₂ , which is smaller than the first structure thickness d ₃₁ is.

The eighth rib 18 has a rib thickness d ₁₈ , which is even smaller than the second rib thickness d ₁₂ , and a rib length l ₁₈ (not shown) that is even smaller than the second rib length l ₁₂ . In the eighth rib 18, a further inner structure in the form of an oil supply 38 is arranged, which has a structure thickness which is even smaller than the second structure thickness d ₃₂ .

The first rib 11, the sixth rib 16 and the 22nd rib 22 are identical, at least substantially, to one another. The eighth and tenth ribs 18, 20 are also, at least substantially, identical to one another. The remaining ribs 12-15, 17, 19, 21 and 23, in particular so the second rib 12 and the fourth rib 14, are also, at least substantially, identical to each other.

Thus, an internal structure in the form of an air supply (compare 31), support strut (compare 32) or oil supply (compare 38) is arranged in each of the ribs 11-23. In addition, all ribs 11-23 each have a non-deflecting outer profile.

The Rippendicken- / length ratio d / L of the ribs 11-23, at least substantially constant, in particular the Rippendicken- / length ratios d ₁₁ / L _11, d ₁₂ / d ₁₈ and l ₁₂ / l _18, at least substantially, equal.

In the Fig. 1 With regard to circumferential positions of the ribs and with respect to the circumferential positions and dimensions of the ribs, the rib arrangement shown has a symmetry with a count of n = 1, ie the rib arrangement is for the first time again congruent with a 360 ° rotation.

The ribs 11-23 are distributed unevenly in the circumferential direction. In particular, the distance T ₁₂ between the first rib 11 and the adjacent second rib 12 and the same distances between the adjacent ribs (15, 16), (16, 17), (17, 18), (18, 19 ), (19, 20), (20, 21), (22, 23) and (23, 11) from the distance T ₂₃ between the second rib 11 and the adjacent third rib 13 and the same distances between the adjacent thereto Ribs (13, 14) and (14, 15) from. This results from the fact that the ribs 12, 13, 14, 15, 17, 19, 21 and 23 with support struts (see Fig. 32), which are identical to each other, evenly distributed among themselves and the ribs 11, 16 and 22 and also structurally identical the ribs 18 and 20, which are also identical to each other, are only present where an air or oil supply is provided, and are therefore unevenly distributed in the circumferential direction, or such thicker, longer or thinner, shorter ribs are dispensed with at the corresponding point of the circumferential graduation , Alternatively, the ribs 12-15, 17, 19, 21 and 23 may be unevenly distributed among each other, as exemplified by a dashed rib 14 '.

With 100, 200 two flow cross sections or compressors or turbines are indicated, which are connected by the transition channel.

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

1

radially outer surface

2

radially inner lateral surface

11

first rib

12

second rib

13-23

third-thirteenth rib

31

Air supply (first inner structure)

32

Support strut (second inner structure)

38

Oil supply (internal structure)

100, 200

Cross-sectional flow / compressor / turbine

A ₁₁ , A ₁₂

outer profile

₁₁

first rib thickness

d ₁₂

second rib thickness

d ₁₈

rib thickness

d ₃₁

first structure thickness

d ₃₂

second structure thickness

₁₁

first rib length

l ₁₂

second rib length

T ₁₂

distance

T ₂₃

distance

Claims (10)

Flow duct for a turbomachine, in particular a gas turbine, with a plurality of ribs (11-23) which are arranged between a radially inner jacket surface (2) and a radially outer jacket face (1) of the flow duct and are distributed in the circumferential direction, a first ( 11) of the ribs has a first rib thickness (d ₁₁ ) and a first rib length ( ₁₁ ) and a second (12) of the ribs has a second rib thickness (d ₁₂ ) and a second rib length ( ₁₂ ), the second rib length being smaller than the first rib length and / or the second rib thickness is smaller than the first rib thickness, and wherein in the first rib a first inner structure (31) having a first structure thickness (d ₃₁ ) and in the second rib a second inner structure (32) disposed having a second structure thickness (d ₃₂ ) which is smaller than the first structure thickness; and or
a distance (T ₁₂ ) in the circumferential direction between the first and of this adjacent second rib and a distance (T ₂₃ ) in the circumferential direction between at least two adjacent (12, 13) of the ribs differ from each other and at least one of these ribs a non-deflecting outer profile (A ₁₁ , A ₁₂ ) and / or an inner structure (32) is arranged in it. A flow channel according to the preceding claim, characterized in that for at least a pair of the plurality of ribs a deviation between a ratio of rib thickness divided by a rib length of one of these ribs and a ratio of rib thickness divided by a rib length of the other of these two ribs is 15% or less is, wherein in this one rib, an inner structure is arranged with a structure thickness which, in particular by at least 1% and / or at most 200%, smaller than a structural thickness of an inner structure which is arranged in this other rib, and wherein the rib length of these a rib, in particular by at least 1% and / or at most 200%, smaller than the rib length of these other of the two ribs and / or the rib thickness of this one rib, in particular by at least 1% and / or at most 200%, smaller than the rib thickness of these other of the two ribs. Flow channel according to one of the preceding claims, characterized in that the two distances differ from each other by at least 1% and / or at most 200%. Flow channel according to one of the preceding claims, characterized in that the symmetry of the flow channel in a region between the inner and outer lateral surface due to the respective circumferential positions and / or the respective dimensions of each of the plurality of ribs has a count n, where n ≤ 8, n ≦ 7, n ≦ 6, n ≦ 5, n ≦ 4, n ≦ 2 and / or n = 1. Flow channel according to one of the preceding claims, characterized in that at least one of the inner structures at least one support strut (32) and / or a passage passage (31) for passage of gas and / or liquid and / or at least partially integral with the rib, in the it is arranged, or is manufactured separately from this. Flow channel according to one of the preceding claims, characterized in that the first rib and / or the second rib has a non-deflecting outer profile (A ₁₁ , A ₁₂ ). Flow channel according to one of the preceding claims, characterized in that at least one group (12-15, 17, 19, 21, 23) is identical in construction to the plurality of ribs in the circumferential direction uniformly and / or at least one group (11, 16, 22; 20) of identical construction of the plurality of ribs is distributed unevenly in the circumferential direction. Transition duct according to one of the preceding claims for connecting an upstream flow cross section (100) with a radially offset downstream flow cross section (200) and / or two compressors or two turbines (100, 200) of the turbomachine. Turbomachine, in particular gas turbine, with at least one flow channel according to one of the preceding claims. An aircraft engine with a gas turbine according to the preceding claim.

Images