EP3492701B1 - Turbomachine flow channel - Google Patents

Description

The present invention relates to a method for producing a flow channel for a turbomachine as well as a flow channel and a turbomachine, in particular a gas turbine, with the flow channel.

From the US 8,061,969 B2 a turbine intermediate casing with support struts and a guide grille following this downstream is known with a number of guide vanes that is larger than the number of support struts or hollow profiles.

GB 2 226 600 A discloses a turbine assembly having an annular shroud and support rib assembly that provides mechanical strength to the turbine assembly and supports the rear rotor bearing. The turbine assembly also includes an exhaust stator downstream of the shroud and support rib assembly.

Another arrangement is from the document US20150260103A1 known. An object of the present invention is to improve a turbomachine.

This object is achieved by a method with the features of claim 1 or a flow channel with the features of claim 5. Claim 12 protects a turbomachine with at least one flow channel described here. Advantageous embodiments of the invention are the subject of the subclaims.

• ein Leitgitter mit mehreren in Umfangsrichtung verteilten bzw. nebeneinander bzw. aufeinanderfolgend angeordneten Leitschaufeln zur Strömungsumlenkung und mit Strömungspassagen, die jeweils durch zwei aufeinanderfolgende (dieser) Leitschaufeln begrenzt sind; und
• eine Stützrippenanordnung mit mehreren Stützrippen, die in einer Ausführung jeweils eine radial innere und eine radial äußere Mantelfläche des Strömungskanals miteinander verbindet, insbesondere gegeneinander abstützt bzw. hierzu bzw. zur Übertragung von Druck- und/oder Zuglasten eingerichtet ist bzw. verwendet wird, und/oder fest mit einem Gehäuse der Turbomaschine verbunden ist.

According to one embodiment of the present invention, a flow channel for a, in particular a, turbomachine, in particular an axial turbomachine, in particular a gas turbine, in particular an aircraft engine

• a guide grille with a plurality of guide vanes distributed in the circumferential direction or arranged next to one another or one after the other for flow deflection and with flow passages which are each delimited by two successive guide vanes; and
• a support rib arrangement with a plurality of support ribs, which in one embodiment each have a radially inner and a radially outer lateral surface of the flow channel connects to each other, in particular is supported against each other or is set up or used for this purpose or for the transmission of pressure and / or tensile loads, and / or is firmly connected to a housing of the turbomachine.

In one embodiment, an axial direction is parallel to a rotation or

(Main) machine axis of the turbomachine, the circumferential direction corresponding in particular to a direction of rotation (of a rotor or at least one running grid following the guide grid) of the turbomachine, a radial direction in particular perpendicular to this axial and circumferential direction. In one embodiment, a first element is downstream of a second element if it is (axially) closer to an outlet of the flow channel or the turbomachine than the second element. Accordingly, in one embodiment, a first element is upstream of a second element if it is (axially) closer to an inlet of the flow channel or the turbomachine than the second element.

In one embodiment, one or more of the support ribs have flow resistance-reducing, in particular symmetrical or asymmetrical, outer profiles; in a further development, the support rib(s) is/are each covered with a flow resistance-reducing hollow profile; in another development, the flow resistance-reducing outer profile is integral with a Core of the support rib is formed. As a result, in one embodiment, a pressure loss and/or vibration excitation can be advantageously reduced. In one embodiment, the guide vanes of the guide grille each have a pressure side and a different suction side for flow deflection.

According to one embodiment of the present invention, when designing the flow channel, a design of at least one (of) the flow passage(s), which is downstream of a support rib, in particular adjacent, is adapted to this support rib in such a way that a pressure loss, in particular at least between an upstream front edge of the support rib and a downstream rear edge of one of the guide blades delimiting this flow passage, and / or a vibration excitation, in particular of the support rib, the guide blades delimiting the flow passage and / or a running grid axially following the guide grille, reduced, in particular minimized, for at least the majority of all supporting ribs of the supporting rib arrangement successive in the circumferential direction, a design of a flow passage of the guide grid downstream of this supporting rib, in particular adjacent, is adapted to this supporting rib in order to avoid a pressure loss and/or vibration excitation to reduce, in particular to minimize.

In one embodiment, the support rib(s) and the downstream flow passage(s) or upstream leading edges of the guide vanes delimiting them are spaced apart axially or by an axial gap.

Additionally or alternatively, in one embodiment for the support rib(s), there is a distance between this support rib, in particular its downstream rear edge, and the flow passage downstream of it, the design of which is or is adapted to this support rib in order to reduce a pressure loss and/or vibration excitation , in particular axially and/or in the circumferential direction, smaller than all other flow passages of the guide grille. In other words, in one embodiment, in particular for at least the majority of all supporting ribs of the supporting rib arrangement successive in the circumferential direction, there is one or the flow passage downstream of a supporting rib, the design of which is adapted to this supporting rib in order to reduce a pressure loss and/or vibration excitation. is, (in each case) the flow passage of the guide grille closest or adjacent to this support rib downstream behind the support rib arrangement.

In this way, in one embodiment, the efficiency and/or the service life of the turbomachine can be improved.

Adapting the design of several of the flow passages downstream of a support rib to these support ribs in order to reduce a pressure loss and/or vibration excitation includes positioning this flow passage in the circumferential direction relative to this support rib in such a way that a wake of the support rib intersects an inlet cross section of the flow passage in a central region of the inlet cross section.

According to the invention, for at least the majority of all successive support ribs of the support rib arrangement in the circumferential direction, one or the flow passage that is downstream of this support rib, in particular adjacent, is positioned relative to this support rib in the circumferential direction in such a way that a wake of the support rib Entry cross section of the flow passage intersects in a central area. A flow passage positioned in this way relative to a support rib is also referred to in the present case as (the) flow passage fed by this support rib for more compact representation or clear identification.

In one embodiment, the wake of a support rib is limited in a conventional manner by the two streamlines that extend from sides of the support rib that are opposite one another in the circumferential direction. In one embodiment, the skeleton line or profile center line of a support rib is, in a conventional manner, the connecting line of the circle centers inscribed in a profile or a cross section of the support rib. In one embodiment, the end region of the skeleton line extends from a downstream rear edge of the support rib over a maximum of 25%, in particular a maximum of 10%, in one embodiment a maximum of 5%, of the length of the skeleton line. In one embodiment, the inlet cross section of a flow passage extends, in particular in the circumferential direction, between the upstream front edges of the guide vanes delimiting the flow passage, its central area in one embodiment extends over at most 80%, in particular at most 60%, and / or at least 10%, in particular at least 25 %, of the inlet cross section or its width in the circumferential direction and / or is equidistantly spaced (in the circumferential direction) from the two leading edges of the guide vanes delimiting the flow passage.

As a result, in one embodiment, the flow is advantageously applied to the guide grid. As a result, in one embodiment, a pressure loss and/or vibration excitation can be particularly advantageously reduced.

In addition to such a circumferential positioning, for at least the majority of all supporting ribs of the supporting rib arrangement that follow one another in the circumferential direction, the adjustment of the design of the flow passage downstream of this supporting rib to the supporting rib upstream thereof in order to reduce a pressure loss and/or vibration excitation, in each case involves changing a shape, in particular also size, of this flow passage compared to one or more of the other flow passages of the guide grid, in particular an additional change in a shape, in particular also size, of several flow passage(s) loaded with support ribs, which are relative to (one) of the support rib(s). ) is or are positioned in the circumferential direction such that a wake of the support rib intersects an inlet cross section of the flow passage in a central area.

According to the invention, at least for the majority of all supporting ribs of the supporting rib arrangement successive in the circumferential direction, a shape, in particular size, of one or the flow passage downstream of this supporting rib, in particular adjacent, the design of which is or is adapted to this supporting rib, different (designed) from at least one other of the flow passages, i.e. additionally a shape, in particular also size, of several flow passages loaded with support ribs, which is or are positioned relative to one of the support ribs in the circumferential direction in such a way that a wake of the support rib has an inlet cross section of the flow passage intersects in a central region, different (designed) from at least one other of the flow passages, which is not a flow passage adjacent to a support rib, in particular is not fed by a support rib.

Through such an adjustment or specific (adapted) profiling of one or more of the flow passages (each) downstream of a support rib, in particular adjacent to or fed by a support rib, a pressure loss can occur in one embodiment and/or vibration excitation can be particularly advantageously reduced.

In one embodiment, this changing the shape, in particular also the size, of at least one (of) the flow passage(s), in particular loaded by a support rib, relative to at least one other (of the) flow passage(s), includes changing, in particular enlarging, one, in particular the middle one , maximum and / or minimum, channel width in the circumferential direction, in one embodiment by at least 1% and / or at most 50%, in particular at most 15%.

Accordingly, in one embodiment, for at least one (of) the support rib(s), in particular at least for the majority of all support ribs of the support rib arrangement successive in the circumferential direction, there is or is one, in particular average, maximum and/or minimum, channel width in the circumferential direction of the flow passage, the design of which is or is adapted to this support rib, in particular the flow passage adjacent to the support rib downstream, from at least one other of the flow passage (designed), in one embodiment by at least 1% and / or at most 50%, in particular at most 15%, in particular i.e. a channel width of the or one or more flow passage(s), which is or are positioned relative to (one) of the support rib(s) in the circumferential direction such that a wake of the support rib intersects an inlet cross section of the flow passage in a central region, of at least one other of the flow passages is different (designed), in particular from the majority of the other flow passages.

As a result, in one embodiment, a wake of the support rib is advantageously guided into the flow passage. As a result, in one embodiment, a pressure loss and/or vibration excitation can be particularly advantageously reduced.

Additionally or alternatively, in one embodiment, changing the size and/or shape of at least one (of) the flow passage(s), in particular loaded by a support rib, relative to at least one other (of the) flow passage(s) includes changing a flow passage-side pressure side of one of the two Guide vanes and/or a suction side on the flow passage side of one of the two guide vanes that delimit one flow passage, and/or the profile of one of these two guide vanes or these two guide vanes relative to the other Flow passage or the guide vane or vanes delimiting it, in particular compared to the majority of the other flow passages.

Changing the shape of a support rib-loaded flow passage(s) relative to at least one other flow passage(s) includes changing a stagger angle of one or both vanes that delimit the flow passage relative to one or both vanes that delimit the other flow passage.

• eine strömungspassagenseitige Druckseite einer der beiden Leitschaufeln, die eine, insbesondere von dieser Stützrippe beschickte, Strömungspassage begrenzen, deren Gestaltung zur Reduzierung eines Druckverlusts und/oder einer Schwingungsanregung an diese Stützrippe angepasst ist bzw. wird, insbesondere eine Strömungspassage begrenzen, die dieser Stützrippe stromabwärts benachbart ist, von der strömungspassagenseitigen Druckseite einer der beiden Leitschaufeln, die eine andere Strömungspassage begrenzen, insbesondere von den strömungspassagenseitigen Druckseiten der Leitschaufeln, die die Mehrzahl der anderen Strömungspassagen begrenzen; und/oder
• eine strömungspassagenseitige Saugseite einer der beiden Leitschaufeln, die eine, insbesondere von dieser Stützrippe beschickte, Strömungspassage begrenzen, deren Gestaltung zur Reduzierung eines Druckverlusts und/oder einer Schwingungsanregung an diese Stützrippe angepasst ist bzw. wird, insbesondere eine Strömungspassage begrenzen, die dieser Stützrippe stromabwärts benachbart ist, von der strömungspassagenseitigen Saugseite einer der beiden Leitschaufeln, die eine andere Strömungspassage begrenzen, insbesondere von den strömungspassagenseitigen Saugseiten der Leitschaufeln, die die Mehrzahl der anderen Strömungspassagen begrenzen; und/oder
• ein Staffelungswinkel einer der beiden Leitschaufeln oder beider Leitschaufeln, die eine, insbesondere von dieser Stützrippe beschickte, Strömungspassage begrenzen, deren Gestaltung zur Reduzierung eines Druckverlusts und/oder einer Schwingungsanregung an diese Stützrippe angepasst ist bzw. wird, insbesondere eine Strömungspassage begrenzen, die dieser Stützrippe stromabwärts benachbart ist, von einem Staffelungswinkel wenigstens einer der eine andere Strömungspassage begrenzenden Leitschaufeln, insbesondere von den Staffelungswinkeln der Leitschaufeln, die die Mehrzahl der anderen Strömungspassagen begrenzen; und/oder
• ein Profil einer der beiden Leitschaufeln oder beider Leitschaufeln, die eine, insbesondere von dieser Stützrippe beschickte, Strömungspassage begrenzen, deren Gestaltung zur Reduzierung eines Druckverlusts und/oder einer Schwingungsanregung an diese Stützrippe angepasst ist bzw. wird, insbesondere eine Strömungspassage begrenzen, die dieser Stützrippe stromabwärts benachbart ist, von einem Profil wenigstens einer der eine andere Strömungspassage begrenzenden Leitschaufeln, insbesondere von den Profilen der Leitschaufeln, die die Mehrzahl der anderen Strömungspassagen begrenzen
  verschieden (ausgelegt).

Correspondingly, in one embodiment for at least one (of) the supporting rib(s), in particular at least for the majority of all supporting ribs of the supporting rib arrangement successive in the circumferential direction,

• a flow passage-side pressure side of one of the two guide vanes, which limit a flow passage, in particular fed by this support rib, the design of which is or will be adapted to this support rib in order to reduce a pressure loss and / or vibration excitation, in particular limit a flow passage which is adjacent to this support rib downstream is, from the flow-passage-side pressure side of one of the two guide vanes that delimit another flow passage, in particular from the flow-passage-side pressure sides of the guide vanes that delimit the majority of the other flow passages; and or
• a suction side on the flow passage side of one of the two guide vanes, which limit a flow passage, in particular fed by this support rib, the design of which is or will be adapted to this support rib in order to reduce a pressure loss and / or vibration excitation, in particular limit a flow passage which is adjacent to this support rib downstream is, from the flow passage-side suction side of one of the two guide vanes that delimit another flow passage, in particular from the flow passage-side suction sides of the guide vanes that delimit the majority of the other flow passages; and or
• a stagger angle of one of the two guide vanes or both guide vanes, which limit a flow passage, in particular fed by this support rib, the design of which is or will be adapted to this support rib in order to reduce a pressure loss and/or vibration excitation, in particular delimiting a flow passage which is adjacent to this support rib downstream from a stagger angle of at least one of the guide vanes delimiting another flow passage, in particular from the stagger angles of the guide vanes , which limit the majority of other flow passages; and or
• a profile of one of the two guide blades or both guide blades, which limit a flow passage, in particular fed by this support rib, the design of which is or will be adapted to this support rib in order to reduce a pressure loss and / or vibration excitation, in particular limit a flow passage, which this support rib is adjacent downstream, from a profile of at least one of the guide vanes delimiting another flow passage, in particular from the profiles of the guide vanes which delimit the majority of the other flow passages
  different (designed).

In one embodiment, the stagger angle is the angle that the profile chord of the guide vane includes with the axial or circumferential direction.

As a result, in one embodiment, a wake of the support rib is advantageously guided in the flow passage. As a result, in one embodiment, a pressure loss and/or vibration excitation can be particularly advantageously reduced.

In one embodiment, the guide grille of the flow channel is a guide grille of a turbine of a gas turbine, in a further development the support rib arrangement is arranged in a turbine intermediate housing ("midturbine frame" MTF) for connecting two turbines of a gas turbine, in particular a turbine intermediate housing, which has a high and a middle - or low-pressure turbine or a medium and a low-pressure turbine connects to one another or is set up or used for this purpose.

This represents a particularly advantageous application of the present invention.

Fig. 1

einen Teil eines Strömungskanals einer Turbomaschine nach einer Ausführung der vorliegenden Erfindung; und

Fig. 2

einen Teil der Fig. 1.

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

Fig. 1

a part of a flow channel of a turbomachine according to an embodiment of the present invention; and

Fig. 2

a part of the Fig. 1 .

Fig. 1 shows a part of a flow channel 1 of a turbomachine according to an embodiment of the present invention or a design of the flow channel 1 according to a method according to an embodiment of the present invention.

The flow channel 1 has a guide grid with several guide vanes distributed in the circumferential direction and flow passages delimited by two successive guide vanes, of which in Fig. 1 exemplary guide vanes 20 - 24 and flow passages 50 - 54 (partially) limited by them are shown.

The flow channel 1 further has a support rib arrangement with a plurality of support ribs distributed in the circumferential direction, of which in Fig. 1 By way of example, a support rib 10, which is adjacent to the flow passage 51 downstream, and a support rib 100, which is adjacent to the flow passage 54 downstream, are shown.

In the illustrated embodiment the Fig. 1 the support ribs 10, 100 run parallel to the axial direction, ie they are not arranged or oriented at an angle to the axial direction. In other embodiments, not shown, the support ribs 10 and/or 100 are inclined to the axial direction or oriented in relation to the axial direction, for example with an angle between 5° and 10°, such as 5°, 6°, 7°, 8° , 9° or 10°.

A design of these flow passages 51, 54 adjacent to a support rib downstream is or is respectively adapted to the support rib 10 adjacent to it upstream or 100 adjusted to reduce pressure loss and/or vibration excitation.

For this purpose, the flow passage 51 is or will be in the circumferential direction (vertically in Fig. 1 ) positioned relative to the support rib 10 in such a way that a caster 12 (cf. Fig. 1 ) and a tangent 14 at a point of a downstream end region of a skeleton line 13 of the support rib 10 intersects an inlet cross section E of the flow passage 51 in a central region, as shown in Fig. 2 is shown. In the same way, the flow passage 54 is or will be positioned in the circumferential direction relative to the support rib 100 such that a wake or a tangent in a point of a downstream end region of a skeleton line of the support rib 100 intersects an inlet cross section of the flow passage 54 in a central region ( not shown).

In addition, there is or will be a channel width B in the circumferential direction (cf. Fig. 2 ) of the flow passage 51 is increased compared to the flow passages 50, 52 and 53.

In addition, a flow passage-side pressure side 41 of the guide vane 21, which delimits the flow passage 51, is or is changed or adjusted, in particular compared to the flow passage-side pressure sides 40 and 43 of the guide vanes 20 and 23, which delimit the flow passage 50 and 53, respectively.

In addition, a flow passage-side suction side 32 of the guide vane 22, which delimits the flow passage 51, is or is changed or adapted, in particular compared to the flow passage-side suction sides 30 and 33 of the guide vanes 20 and 23, which delimit the flow passage 50 and 53, respectively.

In addition, the stagger angles β ₅₁ , β ₅₂ of the guide vanes 21, 22, which delimit the flow passage 51, are or are changed or adjusted, in particular compared to the stagger angle β ₅₀ of the guide vanes 20, which delimits the flow passage 50, as in Fig. 2 shown.

The same applies analogously to the flow passage 54 or the guide vanes delimiting it, of which in Fig. 1 only the guide vane 24 is shown.

A running grid 70 of a turbine or a compressor is arranged downstream behind the guide grid with the guide blades 20-24. In the case of a turbine, a running grid 60 of another turbine is arranged upstream in front of the support rib arrangement with the support ribs 10, 100. In the case of a compressor, a compressor guide grid 60 is arranged upstream in front of the support rib arrangement with the support ribs 10, 100.

Although exemplary embodiments have been explained in the preceding description, it should be noted that a variety of modifications are possible. It should also be noted that the exemplary statements are merely examples and are not intended to limit the scope of protection, applications and structure in any way. Rather, the preceding description provides the person skilled in the art with a guideline for the implementation of at least one exemplary embodiment, whereby various changes, in particular with regard to the function and arrangement of the components described, can be made without leaving the scope of protection, as it appears meets the demands.

Reference symbol list

1

flow channel

10

Support rib

11

downstream rear edge of the support rib 10

12

Caster of the support rib 10

13

Skeleton line of the supporting rib 10

14

Tangent to end area of skeleton line 13

20 - 24

vane

30 - 34

suction side

40 - 44

Print page

50 - 54

Flow passage

60

Guide or playpen

70

Playpen

100

Support rib

b

Channel width

E

Entry cross section

β50 - β52

Stagger angle

Claims (12)

1. Method for producing a flow channel (1) for a turbine engine, in particular a gas turbine, which channel has a guide vane assembly comprising a plurality of guide vanes (20-24) distributed in the circumferential direction, and which has flow passages (50-54) each delimited by two successive guide vanes, and which has a support rib arrangement comprising a plurality of support ribs (10, 100), wherein, for at least the majority of all support ribs of the support rib arrangement that follow one another in the circumferential direction, a design of a flow passage (51, 54) of the guide vane assembly which is downstream of this support rib is adapted to this support rib in order to reduce a pressure loss and/or a vibration excitation, characterized in that adapting the design of the plurality of flow passages to the support ribs which are respectively downstream thereof comprises positioning this flow passage (51, 54) relative to this support rib (10, 100) in the circumferential direction such that a wake (12) intersects an inlet cross section (E) of the flow passage in a central region, and changing a shape of this flow passage with respect to at least one other of the flow passages (50, 52, 53) which is not a flow passage adjacent to a support rib, wherein changing the shape comprises changing a stagger angle (ß₅₁, ß₅₂) of at least one of the two guide vanes (22) which delimit this flow passage with respect to a guide vane which delimits another flow passage (50, 52, 53).
2. Method according to the preceding claim, characterized in that adapting the design of at least one of these flow passages to the support rib downstream thereof comprises changing a shape of this flow passage (51, 54) with respect to at least one other of the flow passages (50, 52, 53).
3. Method according to the preceding claim, characterized in that changing the size and/or shape of the one flow passage (51, 54) with respect to the at least one other flow passage (50, 52, 53) comprises changing, in particular increasing, a channel width (B) in the circumferential direction
   and/or changing a flow-passage-side pressure side (41, 44) of one of the two guide vanes (21, 24) and/or a flow-passage-side suction side (32) of one of the two guide vanes (22) which delimit the one flow passage, and/or profile of at least one of these two guide vanes (21, 22, 24) with respect to the other flow passage (50, 52, 53) or the guide vane or guide vanes (20, 23) delimiting said flow passage.
4. Method according to any of the preceding claims, characterized in that the guide vane assembly is an inlet guide vane assembly of a turbine of a gas turbine, in particular the support rib arrangement is arranged in a turbine intermediate casing for connecting two turbines of a gas turbine.
5. Flow channel (1) for a turbine engine, in particular a gas turbine, which channel has a guide vane assembly comprising a plurality of guide vanes (20-24) distributed in the circumferential direction, and which has flow passages (50-54) each delimited by two successive guide vanes, and which has a support rib arrangement comprising at least one support rib (10, 100), wherein the flow channel is produced according to a method according to any of the preceding claims.
6. Flow channel (1) according to claim 5, wherein, for at least the majority of all support ribs of the support rib arrangement that are successive in the circumferential direction, a flow passage (51, 54) which is respectively downstream of, in particular adjacent to, this support rib (10, 100) is positioned relative to this support rib in the circumferential direction such that a wake (12) intersects an inlet cross section (E) of the flow passage in a central region, wherein a shape of this flow passage is different from at least one other of the flow passages, wherein a stagger angle (ß₅₁, ß₅₂) of one of the two guide vanes which delimit a flow passage is different from at least one other of the flow passages.
7. Flow channel (1) according to either claim 5 or claim 6, wherein a size of this flow passage is different from at least one other of the flow passages.
8. Flow channel (1) according to any of claims 5 to 7, wherein a channel width (B) of this flow passage in the circumferential direction is different from at least one other of the flow passages.
9. Flow channel (1) according to any of claims 5 to 8, wherein a flow-passage-side pressure side (41, 44) of one of the two guide vanes which delimit this one flow passage is different from at least one other of the flow passages.
10. Flow channel (1) according to any of claims 5 to 9, wherein a flow-passage-side suction side (32) of one of the two guide vanes which delimit this one flow passage is different from at least one other of the flow passages.
11. Flow channel (1) according to any of claims 5 to 10, wherein a profile of at least one of the two guide vanes which delimit this one flow passage is different from at least one other of the flow passages.
12. Turbine engine, in particular a gas turbine, comprising at least one flow channel according to any of the preceding claims.

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