CA2833376A1

CA2833376A1 - Axial turbomachine stator with segmented inner shell

Info

Publication number: CA2833376A1
Application number: CA2833376A
Authority: CA
Inventors: Herve Grelin
Original assignee: Techspace Aero SA
Current assignee: Safran Aero Boosters SA
Priority date: 2012-11-27
Filing date: 2013-11-18
Publication date: 2014-05-27
Anticipated expiration: 2033-11-18
Also published as: EP2735707A1; RU2561794C2; RU2013152393A; EP2735707B1; CN103835771A; US20140147262A1; CA2833376C; CN103835771B

Abstract

A compressor stator of an axial turbomachine is described, the stator comprising an inner shell formed of a plurality of annular segments arranged end to end, a layer of abradable material applied on the inner face of the shell, and an annular array of blades connected to the shell. The stator comprises at least one strip located in the layer of abradable material and extending from either side of the junctions between two adjacent annular segments. The inner tips of the blades have hooks mating mechanically with the strip.

Description

AXIAL TURBOMACHINE STATOR WITH SEGMENTED INNER SHELL
Field [0001] The invention relates to an axial turbomachine. More particularly, the invention relates to a stator of an axial turbomachine comprising a segmented inner shell. The invention also relates to a stator assembly process. The invention also relates to an axial compressor.
Background [0002] In order to guide an annular flow, an axial turbomachine is fitted with coaxial shells defining the inside and outside of the flow. In a stator, internal shells are essentially connected to the stator blade tips. They form cylindrical walls having openings through which the stator blade tips are inserted so as to fix them.

[0003] The openings are larger in order to facilitate inserting the blade tips, the gaps then having to be sealed.

[0004] To ensure a seal between the compressor stages, a layer of abradable material is deposited on each internal surface of the inner shells. These layers are intended to be flush with the tips of the radial fins which are formed on the rotor. The section of the inner shells may form a U so as to have an inner annular groove holding the layer of abradable material.

[0005] Patent EP 2196629 Al discloses an inner ring of a bladed stator of a turbomachine. The shell has a U-shaped cross section in which the recess holds a layer of abradable material. The inner shell comprises a plurality of shell segments joined end to end. Their interfaces have surfaces designed to marry with the blades' aerodynamic surfaces. These segments have projections on one side and recesses on the other. The projections on one segment can mate with the recesses of an adjacent segment so that they can interlock.

[0006] Due to the relative flexibility of the abradable material and configuration of the projections, the segments are substantially movable relative to each other. However, in operation, such a shell is subjected to frequency excitations. As a consequence of this, the inner shell can develop destructive vibrational modes. In addition, the projections and recesses have a large radial thickness that affects the thickness of the segments. This need for an increased amount of material increases the weight of the shell and therefore affects its vibrational response.
Summary The technical problem [0007] The invention aims to solve at least one of the problems present in the prior art. More particularly, the invention aims to improve the vibrational behaviour of a stator with a segmented inner shell. The invention also aims to improve the construction of stators, particularly in terms of the connections between the blades and the inner shell.
Technical solution [0008] The invention relates to a stator of an axial turbomachine compressor comprising an annular row of blades extending radially, an inner shell through which the inner tips of the blades pass, the said annular shell being formed of segments arranged end to end, wherein it further comprises at least one strip extending circumferentially along the inner surface of the shell and mating with a means of engaging on the inner tips of the blades for their retention, the said strip(s) extending continuously along at least two adjacent annular segments.

[0009] According to an embodiment, the strip(s) is/are spaced from the inner surface of the shell, the said surface being preferably covered with a layer of abradable material embedding the strip(s).

[0010] According to an embodiment, the strip(s) extend(s) substantially parallel to the inner shroud.

[0011] According to an embodiment, the inner shell has an annular groove open to the interior which houses the layer of abradable material.

[0012] According to an embodiment, the layer of abradable material is continuous across the junctions between the segments.

[0013] According to an embodiment, the inner shell is made of metal or a composite material.

[0014] According to an embodiment, the or at least one of the strips has a flat section, the section preferably being solid.

[0015] According to one alternative, the or at least one of the strips has a circular section, possibly the, or at least one, strip is a wire or cable.

[0016] According to an embodiment, the strip or each of the strips extends over at least a quarter, preferably one third, more preferably one half, of each of two adjacent annular segments.

[0017] According to an embodiment, the strip(s) form(s) an open ring.

[0018] According to an embodiment, the means for engaging the inner tips of the blades comprise openings and/or hooks mating with the strip(s).

[0019] According to an embodiment, the means of engaging are remote from the upstream and downstream edges of the shell, the means of engaging being preferably substantially central on the shell in an axial direction.

[0020] According to an embodiment, portions of the means of engaging mating with the strip(s) have lengths in an axial direction which are greater than 100%, preferably 200%, of the width of the strip(s) so as to allow some variation in the positioning of the means of engaging along the said direction.

[0021] According to an embodiment, the strip(s) has/have a profile matching that of the profile of the shell.

[0022] According to an embodiment, the profile(s) of the strip(s) between two adjacent blades correspond(s) to that of the shell.

[0023] According to an embodiment, the shell includes at least four annular segments, the strip or one of the strips spanning at least a twentieth, preferably at least an eighth, more preferably a quarter of the inner shell.

[0024] According to an embodiment, the strip is a metallic material, preferably titanium, steel or aluminium.

[0025] According to an embodiment, the means for engaging the inner tips of the blades comprise hooks in which the throat is oriented in an axial direction.

[0026] According to an embodiment, the hooks have a lip in their throat, designed to restrain the strip(s) axially.

[0027] According to an embodiment, the hooks can be notches made laterally on the inner tips of the blades.

[0028] According to an embodiment, the stator comprises boundary seals at the junction between the openings and the blade tips, the beads of which extend radially inwardly from the inner surface of the inner shell, the strip(s) being spaced from the seals.

[0029] According to an embodiment, the width of the section of the strip(s) is greater than 10% of the width of the section of the inner shell, preferably greater than 20%, even more preferably greater than 30%.

[0030] According to an embodiment, the stator includes several strips whose ends overlap radially and possibly the ends are welded at the overlaps.
Alternatively, the stator may comprise several strips the ends of which are spaced from each other.

[0031] According to yet another embodiment, the material of the strip(s) is substantially free of plastic deformations.

[0032] The invention also relates to a compressor, including that of an axial turbomachine, comprising at least one bladed stator wherein the or at least one stator is in accordance with the invention, the compressor preferably being a low-pressure compressor.

[0033] The invention can modify the frequency response of the inner shell substantially by changing its stiffness at the joint between two segments.
The strip remains flexible and does not form any stiffening completely blocking the junctions between segments. The choice to retain some flexibility is sufficient to contain the destructive vibrational modes of the inner shell.

[0034] The strip is essentially slender. It remains light, which does not change the mass or inertia of the shell affecting its frequency response when excited vibrationally. The invention can act on the low-frequency vibrational modes that are most harmful. The choice of a slender and light strip is advisable since it is complementary to the abradable layer whose potential viscoelasticity can be exploited to dampen high frequency vibrations.

[0035] The invention exploits the presence of the blades to improve the anchoring effects of the strip(s) at the same time as their own anchorages. In this way, the whole is more rigid and prevents low-frequency vibrational modes.
Assembling the stator is thus facilitated by the invention.
Short description of the diagrams [0036] Figure 1 shows an axial turbomachine in accordance with the invention.

[0037] Figure 2 is a sectional view of the compressor of the turbomachine in Figure 1 in accordance with the invention.

[0038] Figure 3 illustrates two annular segments of a stator of the compressor in Figure 1, the stator being in accordance with the invention.

[0039] Figure 4 is a sectional view of the shell of the stator shown in Figure 3.
Description of the embodiments [0040] In the following description, the terms 'inner' or 'internal' and 'outer' or 'external' refer to a position relative to the axis of rotation of an axial turbomachine.

[0041] Figure 1 shows an axial turbomachine. In this case it is a double-flow turbojet. The turbojet 2 comprises a first compression stage, a so-called low-pressure compressor 4, a second compression stage, a so-called high pressure compressor 6, a combustion chamber 8 and one or more turbine stages 10. In operation, the mechanical power of the turbine 10 is transmitted through the central shaft to the rotor 12 and drives the two compressors 4 and 6. Reduction mechanisms may increase the speed of rotation transmitted to the compressors. Further, different turbine stages can be connected to the compressor stages through concentric shafts.
Compressors comprise several rotor blade rows associated with stator blade rows. The rotation of the rotor thus generates a flow of air and progressively compresses it up to the inlet of the combustion chamber 10.

[0042] An inlet fan, commonly designated a 'turbofan' 16, is coupled to the rotor 12 and generates an airflow which is divided into a primary flow 18 passing through the various stages of the turbomachine mentioned above, and a secondary flow 20 passing through an annular conduit (shown in part) along the length of the machine and then rejoins the main flow at the turbine outlet.
The primary flow 18 and secondary flow 20 are annular flows and are channelled through the housing of the turbomachine. To this end, the housing has cylindrical walls or shells that can be internal or external.

[0043] Figure 2 is a sectional view of a low-pressure compressor 4 of an axial turbomachine 2 such as that of Figure 1. Part of the turbofan 18 can be seen, as can the splitter nose 22 between the primary 18 and secondary 20 airflows. The rotor 12 comprises several rows of rotor blades 24, for example three.

[0044] The low-pressure compressor 4 includes several stators, for example four, each containing a row of stator blades 26. Stators are associated with a fan 16 or a row of rotor blades for straightening the airflow so as to convert the velocity pressure of the stream into pressure.

[0045] The stator blades 26 extend substantially radially from an outer housing and can be fixed with a dowel. They are regularly spaced from each other, and have the same angular orientation to the stream. Advantageously, these blades are identical. Optionally, the spacing between the blades can vary locally as can their angular orientation. Some blades in a row can be different from the others.

[0046] The stators each comprise an inner shell 28 to guide the primary flow 18.
The shells 28 each have an annular row of openings. These are evenly distributed over the circumference of the internal shells and the inner tips of the blades pass through them in order to fix the shell. Internal shells 28 have a U-shaped cross section in which the hollow portion points inwards. Internal shells 28 may be made of metal, for example titanium alloy, or a composite material.

[0047] The stators each have an annular layer of abradable material 30 housed in the hollows of the internal shells 28. The abradable layers 30 may be of substantially constant thickness, so as to form a band. These abradable layers 30 are intended to mate by abrasion with lip seals or circumferential fins so as to provide a seal. The layers of abradable material act as a filler and can be structural.

[0048] Figure 3 shows a portion of the stator of the compressor of Figure 2.
The inner shell 28 is essentially formed of a plurality of annular segments 32. It is divided into annular sectors or annular segments, preferably regular. The annular segments 32 are arcuate. They each have a plurality of openings 34 in which the inner tips of the stator blades 26 are inserted. For example, each annular segment 32 can be linked to four blades 26. However, it may be linked to more or less than four blades. The annular segments have the U-shaped section of the inner shell 28, their hollow interior housing the annular layer of abradable material (not shown).

[0049] The annular segments 32 have gaps between them. They can be close together or some distance apart. However they are integral with each other because of the layer of abradable material. This layer creates a physical interface 36 between adjacent annular segments. Optionally, a blade tip may pass through an interface between the annular segments 32.

[0050] The annular segments 32 are substantially rigid with respect to the layer of abradable material so that in the event of deformation or vibration of the inner shell 28, any deformation is concentrated in that portion of the layer of abradable material located at the interface 36 between the annular segments 32.

[0051] Depending on the operating conditions, the vibrations can be amplified so much so that the stator can experience critical mode vibrations that can become destructive. To control the impact of these critical modes, the stator is fitted with strips 38 passing through the interface 36 between the annular segments 32. They are housed in the thickness of the layer of abradable material 30.

[0052] Preferably, the same strip(s) pass(es) though several annular segments.

Optionally, the stator comprises one strip passing along its entire circumference.

[0053] The strip(s) 38 comprise(s) a metallic material. An alloy of titanium or aluminium may be chosen to reduce the weight. A grade of steel can be used to reduce costs. The strip(s) 38 may be (an) extruded strip(s), for example of rectangular cross section. Such (a) strip(s) may have a thickness less than 0.50 mm, and a width of between 2.00 mm and 10.00 mm. The strip(s) can also be circular, possibly comprising a metal wire or cable.

[0054] The strips are solid. They are straight when manufactured. To be mounted in the stator, they are bent to follow the curvature of the inner shell. The materials of which they are made and their sections enable them to be sufficiently flexible to deform elastically when they are bent during assembly.

[0055] The inner tips of the blades 26 have a means of engaging 40. The means of engaging may comprise openings and/or hooks 40. They are hooked to the strip(s) 38 and also allow for radial retention of the blades 26 relative to the shell 28, and optionally also locking the strip(s) axially. The hooks can be lateral notches formed on an upstream or downstream side of a blade, the notch having a substantially constant width.

[0056] Figure 4 shows a cross section of the shell 28 of the stator of Figure 3. The hook 40 defines a cavity 42 axially elongated that can accommodate the strip 38. The hook 40 has a throat 42 located axially in the cavity so as to allow insertion of the strip transversely to its elongation or axially along the stator's axis. The lip to the throat 42 may form a narrowing in the latter.

[0057] The throat 42 is generally adjusted in shape to the section of the strip, so that it has a shape similar to the section of the strip. Nevertheless, the size of the throat is greater than the section of the strip. This particularity enables it adjust to variations in the positioning of the blades, and in particular, their hooks 40. The maximum variation in the axial positioning of the hook 40 can be more than 3.00 mm with respect to a nominal position. The maximum variation in the radial positioning of a hook 40 can be greater than 2.00 mm relative to a nominal position.

[0058] One of the hooks 40 need not be in contact with a strip. One of the hooks 40 may be in contact with a strip substantially axially or radially.

[0059] The strip(s) 38 is/are positioned in the depth of the layer of abradable material 30. It is/They are positioned in the heart of the abradable layer, allowing it/them to be enclosed on all sides. It/They form(s) a core in the layer of abradable material and change(s) its behaviour. Thus, it/they can change the elasticity of the physical junction which is formed by the layer of abradable material 30.

[0060] The mass of the strip(s) is/are negligible compared to that of the combined mass of the shell and the abradable. This mass is less than 5% of the combined mass of the shell and the abradable, preferably less than 1%.
Thus, the addition of the strip(s) does not significantly alter the mass of the whole, and does not introduce any new critical mode frequencies. If the mass had been increased new critical mode frequencies below those already in existence may occur. These new modes and their harmonics increase the risk of damage.

[0061] A silicone seal 44 is formed at the junction between the blades 26 and the openings. It improves sealing and temporarily holds the annular segment 32 against the blades 26 during assembly. It forms a bead which is made before inserting the strip(s) 38. Advantageously, the inner side of the silicone seal 44 is spaced away from the strip(s) 38. This feature improves the embedding of the strip(s) in the abradable material.

[0062] The overall configuration is particularly advantageous since it allows easy assembly of the stator. Such an assembly method is based on the following steps:
a. assemble, or use a pre-assembled, annular array of blades fitted on an exterior medium, an inner shell being fitted to the inner tips of the blades;
b. insert a strip at the inner tips of the blades, the strip being positioned on the axial side of the hook throats. Its ends are each in contact with an inner blade tip, and its central part is at some distance from the blades.
C. bend the middle of the strip 38 so that it comes into contact with the inner tips of the blades along its entire length. The strip is thus curved so as to be parallel with the line of the hook throats.
d. slide the strip axially into the hooks and then release it.
e. fit the layer of abradable material into the inner shell.

[0063} It is worth stressing that steps b), c) and d) can be done in a few seconds for a strip in contact with a dozen blades. The installation time is reduced and reduces the cost of labour.

Claims

1 . Stator of a compressor, of an axial turbomachine comprising:
- an annular ring of blades extending radially;
- an inner shell through which the inner tips of the blades pass, the said shell comprising annular segments arranged end to end;
wherein it further comprises:
at least one strip extending circumferentially along the length of the inner surface of the shell and mating with a means of engaging the inner tips of the blades for their retention, the said strip(s) extending continuously along at least two adjacent annular segments.

2. Stator in accordance with Claim 1, wherein the strip(s) are spaced from the inner surface of the shell..

3. Stator in accordance with Claim 2, wherein the inner surface of the shell is covered with a layer of abradable material embedding the strip(s).

4. Stator in accordance with any one of Claims 1 to 3, wherein the or at least one of the strips has a flat section.

5. Stator in accordance with Claim 4, wherein the flat section is solid.

6. Stator in accordance with any one of Claims 1 to 5, wherein the strip or each of the strips extends over at least a quarter of each of two adjacent annular segments.

7. Stator in accordance with any one of Claims 1 to 5, wherein the strip or each of the strips extends over at least one third of each of two adjacent annular segments.

8. Stator in accordance with any one of Claims 1 to 5, wherein the strip or each of the strips extends over at least one half, of each of two adjacent annular segments.

9. Stator in accordance with any one of Claims 1 to 8, wherein the strip(s) form(s) an open ring.

10. Stator in accordance with any one of Claims 1 to 9, wherein the means of engagement of the inner tips of the blades comprise openings and/or hooks mating with the strip(s).

11. Stator in accordance with any one of Claims 1 to 10, wherein the means of engagement are spaced upstream and downstream of the shell.

12. Stator in accordance with any one of Claims 1 to 10, wherein the means of engagement are spaced upstream and downstream of the shell and are essentially central in the shell in an axial direction.

13. Stator in accordance with any one of Claims 1 to 12, wherein the portions of the means of engagement mating with the strip(s) have lengths in an axial direction which are more than 100% the width of the strip(s) so as to allow a variation of positioning of the means of engagement along the said direction.

14. Stator in accordance with any one of Claims 1 to 12, wherein the portions of the means of engagement mating with the strip(s) have lengths in an axial direction which are more than 200 % the width of the strip(s) so as to allow a variation of positioning of the means of engagement along the said direction.

15. Stator in accordance with any one of Claims 1 to 14, wherein the strip(s) have an annular profile matching that of the profile of the shell.

16. Stator in accordance with Claim 15, wherein the profile of the strip(s) between two adjacent blades matches that of the shell.

17. Stator in accordance with any one of Claims 1 to 16, wherein the shell comprises at least four annular segments, the strip(s) spanning at least a quarter of the inner shell.

18. Stator in accordance with any one of Claims 1 to 16, wherein the shell comprises at least four annular segments, the strip(s) spanning at least one half of the inner shell.

19. Stator in accordance with any one of Claims 1 to 16, wherein the shell comprises at least four annular segments, the strip(s) spanning the entire inner shell.

20. Stator in accordance with any one of Claims 1 to 19, wherein the strip(s) is/are made of a metallic material.

21. Stator in accordance with any one of Claims 1 to 19, wherein the strip(s) is/are made of a metallic material that is titanium, steel or aluminium.

22. Stator in accordance with any one of Claims 1 to 21, wherein the means of engagement of the inner tips of the blades comprise hooks whose throats are oriented in an axial direction.

23. Stator in accordance with Claim 22, wherein the hooks have lips at their throats, designed to restrain the strip(s) axially.

24. Compressor of an axial turbomachine, comprising at least one bladed stator, wherein the or at least one stator is in accordance with any one of Claims 1 to 23.

25. Compressor in accordance with claim 24, wherein the compressor is a low-pressure compressor.

26. Compressor comprising at least one bladed stator, wherein the or at least one stator is in accordance with any one of Claims 1 to 23.