CN103671251B - Blade is connected on the cylindrical rotor of axial flow turbo compressor - Google Patents

Abstract

The method on rotor (4) is connected to the present invention relates to the design of the rotor blade of axial flow turbo compressor (2) (12), more particularly to by blade (12).Blade (12) includes airfoil portion and platform (14) so that blade is connected on rotor (4).Along the main shaft of blade, platform (14) includes first layer and is located at the second layer under first layer relative to aerodynamic surfaces, first layer forms a surface, the surface restraint liquid stream simultaneously surround aerodynamic surfaces, and the second layer is designed to the inner surface of the wall (18) of the rotor (4) in the hole in the rotor (4) to coordinate to fix purpose.

Description

Blade is connected on the cylindrical rotor of axial flow turbo compressor

Technical field

The present invention relates to the compressor of the rotor blade of axial flow turbo-machine, more particularly to axial flow turbo-machine.The present invention It is related to and these blades is connected on the rotor of turbine.The invention also relates to accommodate the turbine rotor of the blade.

Background technology

Patent US3385512A discloses a kind of bladed rotor of axial flow turbo-machine compressor.The rotor includes Support the cylindrical rotor of multiple blade rows.The cylindrical rotor includes being used for the installation groove for often arranging blade.Many blades are arranged On the utility bracket of a section is formed.The latter is by inserting the corresponding recesses in cylindrical rotor and fixed on rotor.Bracket Be included on the surface namely relative with actual blade of its lower surface have can be inserted into it is whole in the groove of cylindrical rotor Body rib.The rib includes groove in each of which opposite.Groove on cylindrical rotor is included in the phase in the groove of cylindrical rotor Two flat springs for answering groove inner periphery to extend.When the utility bracket of each blade is inserted, the front of rib includes taper work face, The taper work face is used to contact each leaf and slided along the latter so as to promote it relative to their the caused elastic force that moves Enter corresponding groove.Once the transverse groove in rib is relative with each leaf, then the elastic force that the latter will rely on them to apply enters It.Each leaf, once into appropriate location, just across on the corresponding recesses for standing in leaf bracket and cylindrical rotor, thereby, it is ensured that blade It is connected on rotor.Such fixing means is interesting but some defects be present.This needs the lot of materials of bracket and cylindrical rotor, Thus the final weight of engine is leveraged, and more importantly, substantially increases centrifugal force, cydariform is thus limit and turns The diameter and maximal rate of son.

Patent US2944326A discloses a kind of method being connected to axial flow turbo compressor blade on rotor.Each leaf Piece reduces with size and platform of its cross section with wedge profile.Moulded in each side of platform to be formed it is fluted.Phase To each blade, rotor wall includes a hole, and the profile in hole is corresponding with the profile of bucket platform.Then each blade insertion rotor A hole in, wherein it is prevented from departing from from direction, because platform and the cone or wedge profile in hole accommodate It.Then, stamping tool, such as stamping machine and punch die are used to apply high pressure on to rotor close to the surface at the edge in hole Power, the edge of its mesopore is equivalent to the transverse concave groove in platform.The purpose of the operation be by formed hole material back into it is flat So that it is guaranteed that it is jammed, especially in the opposite direction mentioned in transverse concave groove in platform.Blade is thus relative to rotor Firmly accommodated in the both direction of radial direction.The connection method is interesting but some defects be present.It requires rotor in its quilt That position being connected on blade is very thick.The principle of blade with cone shape profile platform is installed only to certain thickness The material of degree is possible.It is also genuine in order to which material is back into transverse concave groove.The fixing means be not suitable for substantially by Form the light-duty cylindrical rotor that the thin-walled of cylindrical rotor net is formed.

Patent US2685405A discloses a kind of bladed rotor of Axial Flow Compressor, wherein each blade is hollow And connected with rotor fluid.Each blade includes the platform for forming installation groove.Rotor is interconnected by some Part composition.Installation of the blade on rotor is provided by two adjacent rings of each rows of blades.It is every in the two rings One ring has nicked edge, and otch half profile corresponding to the installation groove of each blade is matched.Each groove And each blade is sandwiched between two mounting rings, the latter is mechanically connected on the remainder of rotor.The rotor of this type It is designed to stage to be in fluid communication.As previously described in detail, the installation of this type needs many materials. Moreover, it also needs to manufacture many parts and needs sizable effort to assemble.

The content of the invention

Technical problem

The blade of axial flow turbo-machine is connected to simple on rotor and again it is an object of the invention to provide a kind of Measure light method.A kind of more particularly it is an object to provide weight being connected to blade on compressor cylindrical rotor Measure light and simple method.

Technical scheme

The present invention relates to axial turbomachine rotor blade, including：For connecting the platform of rotor；It is mutually contradictory and from Two aerodynamic surfaces of main shaft extension of the platform along blade；Form constraint liquid stream and around the table of aerodynamic surfaces Face；And the second layer, it is located at below first layer relative to aerodynamic surfaces and is used to connect blade；Wherein platform The second layer is configured to coordinate to connect the inner surface of rotor wall of the purpose with positioning around the hole of the rotor.

According to a preferred embodiment of the invention, the second layer of platform be configured to in the both sides in hole it is circumferentially positioned The layer of the inner surface of rotor wall directly and/or indirectly coordinates.

According to a preferred embodiment of the invention, the second layer forms the one or more shoulders protruded from the surface of first layer.

According to a preferred embodiment of the invention, the second layer is disposed at least substantially parallel to first layer extension and from the table of the layer Face is protruded so as to form shoulder at its each edge.

According to a preferred embodiment of the invention, the second layer is prominent from the lower surface of first layer and including a positioner example Such as preferably with respect to the hole of rotor circumferential orientation, can be connect with the elongated joining devices machinery for being used to contact with the inner surface of wall Close.

According to a preferred embodiment of the invention, the lower surface of first layer is around the second layer and in the respective surfaces of rotor wall On platform on form support surface.

The invention further relates to the bladed rotor on axial flow turbo-machine, and thus blade is the leaf according to the present invention Piece.

According to a preferred embodiment of the invention, rotor includes the ring part of the wall equipped with row's blade mounting hole, the wall Portion is preferably monoblock type.

According to a preferred embodiment of the invention, rotor structure is generally made up of the wall for foring circular net, close to wall Annulate lamella upstream and/or downstream at, the annulate lamella of wall protrudes relative to the net, and the ring part of the wall preferably corresponds to Single blade and net preferably include at least one circumferential rib, and the circumferential rib is designed in the inner casing with stator vane stage Surface cooperation substantially sealed off.

According to a preferred embodiment of the invention, wall is included between the annulate lamella of the wall and wall to form housing generally diametrically At least one articulamentum of extension.

According to a preferred embodiment of the invention, blade is the blade according to any one of claim 3 and 4, wall The shape of the mounting hole of ring part correspond to bucket platform first layer shape, and the border surface of the liquid stream of the layer and The outer surface of the ring part of wall flushes.

According to a preferred embodiment of the invention, rotor includes acting on the inner surface of bucket platform so that they to be fixed just The pressure apparatus of position, the band that described device preferably at least includes clasp and/or ring-type is formed.

According to a preferred embodiment of the invention, rotor includes the bonder between bucket platform shoulder and rotor wall, example Such as viscose glue.

According to a preferred embodiment of the invention, the mounting hole on the ring part of wall and blade especially their aerodynamic force table Face is constructed such that blade and is inserted through hole from the inside of rotor to fix their purpose.

According to a preferred embodiment of the invention, the outer surface of the ring part of wall include around each mounting hole cavity and Attachment means, wherein cavity are used for the second layer of the first layer for accommodating bucket platform and the bucket platform through the hole, connection The positioner of for example one or more clasps of device and bucket platform coordinates and coordinated with the inner surface in the portion of wall, institute State the preferred annular configuration of device.

It is required that interests

The step of the present invention make it that the device that is connected to turbine blade on rotor is advantageous.Such assembly apparatus by In allowing blade and rotor to be made from a variety of materials so as to have advantage, especially can not possibly implement to weld therebetween In the case of operation.The class component also has the advantages of very light.It is suitable for the rotor of cydariform, that is, substantially by being formed The thin-walled of cusped arch or drum-shaped shell forms, and is particularly provided with the annular relief of wall.These parts have hardening cylindrical rotor with And compensation accommodates the two-fold advantage of the difference in height needed for the inner casing of stator vane.It is particularly suitable for according to the blade of the present invention this kind of The rotor of type.They have used the ledge of wall to accommodate blade so as to be connected them but not need extra any material Or enhancing.

Brief description of the drawings

Fig. 1 be jet engine axial flow turbo-machine low-pressure compressor section part sectioned view, each blade and turn Son is the blade and rotor according to first embodiment of the invention.

Fig. 2 is the profile of the turbine rotor in Fig. 1, show selectable turn according to a first embodiment of the present invention Blades connection method.

Fig. 3 is the perspective view according to an one exemplary embodiment of the blade of first embodiment of the invention.

Fig. 4 is the part sectioned view according to the axial turbomachine rotor of second embodiment of the invention.

Fig. 5 is the perspective view of the rotor blade in Fig. 4 according to second embodiment of the invention.

Fig. 6 be Fig. 4 in bladed rotor along 6-6 profile.

Embodiment

Fig. 1 show the front portion of the axial flow turbo-machine 2 of jet engine.Show the air inlet on rotor 4 Fan 6.Immediately the downstream of fan 6 be the air-flow for flowing through fan 6 water conservancy diversion front edge of board 8.The fluid discussed be divided into through Sidestream outside the main flow and main flow and compressor of the different compression stages of compressor.Compressor includes being made up of stator vane 10 A series of stator levels.Rotor 4 supports a series of rotor blade rows 12, each rotor blade row and the stator positioned at immediately downstream Blade row forms the compression stage of compressor together.

Rotor 4 is the mainly cylindrical rotor by being formed around the wall 16 of its rotary shaft rotational symmetry.The wall forms correspondingly In the housing of the overall shape of Gothic arch cylindrical rotor.However, it has the lug boss corresponding with securing the row of blade 12 18.These annular reliefs 18 cause blade be fixed thereon and expose their platform 14, limit by compressor along Rotor wall is until the main flow of the inner housing 20 of adjacent stator blades 10.Housing 20 is supported by stator vane 12 and including wear-resisting material Material 22, high-abrasive material 22 substantially together provides sealing with the lip packing 24 on the wall 16 of rotor 4.

The lug boss 18 of wall includes hole, and blade 12 is inserted in the hole and remained at.Each blade 12 includes platform 14, Platform 14 is used for directly in the inside or inner surface of the edge in the hole and wall 18 coordinating.In fact, it can such as see in Fig. 1 , the platform 14 of rotor blade 12 is included in the inner surface of the lower floor that upstream and downstream edge forms shoulder, these shoulders and wall It is in contact.They keep in the machinery for radially providing blade.Such shoulder can also be formed at other edges of platform 14, Namely it is formed circumferentially on edge.Them are not shown in Fig. 1, because Fig. 1 is the longitudinal sectional drawing of rotor.

Rotor blade 12 from the inside of cylindrical rotor therefore by inserting to position；Blade airfoil is firstly inserted into accordingly Kong Zhong, then platform insertion is had in the hole of the retaining layer contacted with the inner surface of rotor wall so as to locating platform.Rotor leaf Piece 12 can also be secured in position by the way that other devices are for example gluing.Keeping the shape of platform 14 ensures corresponding to centrifugal force The radial positioning of blade on direction.During rotation, these power are great enough that they deviate from and act on its on blade Its power, such as aerodynamic force and the power relevant with blade own wt.When stopping or even low speed, centrifugal force is zero or very little And therefore rotor blade is fixed critically important by other devices.But the power that blade is subjected in these cases compare with from The relevant power of mental and physical efforts is much lower.

Notice being sized to so that being interference fitted between the two for bucket platform and the housing bore on wall 18. In this case, platform and/or the edge in the hole on wall 18 can be tapers so that it is guaranteed that folder when rotor blade assembles Tightly.

Fig. 2 show the flexible method being connected to blade on rotor of the first embodiment of the invention according to Fig. 1. Fig. 2 only shows rotor with section.

The first rotor blade row 12 is cut by the circle having in respective shapes groove being contained on the inner side of platform 14 Face clasp 26 is secured in place.The ring is preferably made up of elastic metallic material such as spring steel.It is constructed such that it once In to stress state is on platform during the position of applying power, these power are generally radially outwards pointed to from rotor.

Second rotor blade row 12 is still secured in position by clasp, but is specifically substantially rectangular section clasp 28. It is also accommodated in the groove with respective shapes being formed on the inside of platform.It is also configured to so that it is flat in support The position of platform is in stress state.

Third trochanter blade row 12 is secured in position by the band 30 extended along in most of bucket platform length.Given band Width, what corresponding groove was not required.

Each attachment means shown in Fig. 2 for example and for example can be bonded and/or clamped mutually or with other devices It is used in combination.

Fig. 3 is the perspective view of the blade of the first embodiment of the invention shown in Fig. 1 and Fig. 2.Rotor blade 12 substantially by Aerodynamic force layer 32 and platform 14 are formed.The latter includes forming flow surfaces and around the first upper strata 34 of aerodynamic force layer 32.Should Surface can be parallelogram shape, be rectangular shape more particularly.Its thickness is approximately equivalent to rotor wall lug boss 18 (Fig. 1 and Fig. 2) thickness, be more particularly comparable to rotor wall just accommodate blade hole edge thickness. Platform 14 also includes the second layer 36 below first layer.The second layer 36 covers the scope of first layer and at least Shoulder is formed in one layer 34 of two opposite edges.Under Fig. 3 particular case, second layer shape on four edges of first layer Into shoulder.These shoulders are used to the inner surface in the edge contact wall in the hole for accommodating blade.

Circular cross-section groove 38 is laterally formed on the inner surface of platform 14, is in the second layer 36 in this case Inner side.The groove is used to coordinate the clasp 26 shown on the first rotor row in clasp such as Fig. 2 of annular.

The second layer of bucket platform can take many forms, as long as it can provide the mode of blade described in machinery positioning. In fact, the replacement as the scope for covering first layer, it may be defined as limiting the support of shoulder.

The upstream and downstream edge of the second layer 36 has the curved surface for the inner surface profile for following the wall contacted.

Bucket platform and the rotor wall portion coordinated with blade are configured to such form so that forming flow surfaces The surface of first layer 34 flushes with the outer surface of described wall portion.

Fig. 4-6 show the second embodiment of the present invention.Fig. 4 is the part sectioned view of axial turbomachine rotor, shown For blade is assembled in rotor wall.Fig. 5 is the perspective view of the blade shown in Fig. 4.Fig. 6 is bladed rotor edge in Fig. 4 The view of line 6-6.

For identical or corresponding part, the reference in Fig. 1-3 of first embodiment is equally used for the second implementation In Fig. 4-6 of example；But these marks both increase 100.For identical part, reference is implemented with reference to first Those marks of example.

Rotor 104 shown in Fig. 4 is similar to the rotor shown in Fig. 1 and Fig. 2.However, the different walls for being to accommodate blade 112 Lug boss 118.As the replacement with substantially prismatic hole, wall portion 118 corresponds roughly to platform including cross section herein The cavity of cross section and the hole less than the cavity.

The platform 114 of blade 112 includes first layer 134, similar to the platform in first embodiment first layer 34 (referring to Fig. 3).It also includes the second layer 136 below first layer 134.The second layer 136 from the bottom of first layer extend so as to It is prominent.It is used to through the hole in wall lug boss 118 so as to connect blade.It includes being used for being supported in wall portion 118 The hole 138 that attachment means on surface coordinate.Hole 138 is circumferentially-oriented in the rotor.Fig. 6 is shown through on rotor blade row The clasp 126 in the hole of some adjacent blades platforms.Clasp 126 can extend in whole circumference, form multi-turn or can be more Section with a small number of blades in a row so as to only coordinate.

The second layer protruded from the bottom surface of first layer can be taken different from the form shown in Fig. 4-6.Determine on the second layer Position device is similarly such.Hole can take other forms, including be differently oriented.Several holes are provided on the second layer It is possible.Positioner can also be formed by the suitable exterior contour of the second layer.The latter may, for example, be T-shaped profile, button Ring or the locking bar of respective shapes can be matched so that it is guaranteed that holding of the blade on rotor.

It can provide for the clamping device for applying tension force on the second layer.They can be integrated into positioner ( In this case be hole 138) coordinate attachment means in (being in this case the clasp 126 in Fig. 4-6 example).Connection Device can it is at least one with the contact surface of the second layer of platform on have taper so as to when positioning the fixing device to The second layer applies tractive force.Alternatively, or in addition, clamping device can be as the dress being fixed on the inner surface of wall The supporter put.

The blade of the present invention, it is, two embodiments especially described above, can use the material different from rotor To manufacture.Especially, they can be manufactured with composite, particularly the composite with organic matrix.Rotor in itself may be used To be made of metal material such as titanium.Therefore bladed rotor very light can provide optimal blade connection simultaneously, Particularly suitable for the differential expansion between material used in compensation.

Blade can also include one or more metal inserts made of composite, particularly in the second podium level On, second podium level including during turbine operation in some cases can be by very big pressure.

Claims (17)

1. the bladed rotor (4) of axial flow turbo-machine, including：

- blade (12)；

- the rotor structure being made up of the wall (16) for foring circular net；

- be provided with row's blade mounting hole wall (16) wall portion (18), at the upstream and/or downstream close to the wall portion, The wall portion (18) protrudes relative to circular net,

Wherein each blade (12) includes：

- be used to for blade to be connected to platform (14) on rotor (4)；

- it is mutually contradictory and from the platform (14) along blade main shaft extension two aerodynamic surfaces (32)；

Along the main shaft of blade, the platform (14) includes：

● first layer (34), it forms a surface to constrain liquid stream and surround the aerodynamic surfaces (32), and

● the second layer (36), it is located at below the first layer (34) and is used to relative to the aerodynamic surfaces (32) Connect the blade；

Wherein

The second layer (36) of the platform (14) forms the one or more shoulders protruded from the surface of the first layer (34) Portion and in order to connect the interior of the blade purpose and the wall portion (18) of the rotor (4) of the respective aperture in the wall portion Surface engagement.

2. bladed rotor (4) as claimed in claim 1, wherein, the second layer (36) of the platform (14) with Directly coordinate in the inner surface of the circumferentially positioned wall portion in the opposite side in the hole (18).

3. bladed rotor (4) as claimed in claim 1 or 2, wherein, the second layer (36) is disposed at least substantially parallel to Part I extends and protruded from the surface of the part so as to form shoulder at its each edge.

4. bladed rotor (4) as claimed in claim 1, wherein, the shape of the mounting hole of the wall portion (18) is corresponding In the shape of the first layer (34) of the platform (14) of the blade (12), and the liquid stream of the first layer (34) The outer surface of border surface and the wall portion (18) flushes.

5. bladed rotor (4) as claimed in claim 1, wherein, the bladed rotor includes acting on institute State the pressure applying means so that they to be secured in position, described device bag on the inner surface of the platform (14) of blade (12) Include at least one clasp (26,28) and/or the band (30) of annular configuration.

6. bladed rotor (4) as claimed in claim 1, wherein, the bladed rotor is included in the leaf Bonder between the shoulder and the wall portion (18) of the platform (14) of piece (12).

7. bladed rotor (4) as claimed in claim 1, wherein, the mounting hole of the wall portion (18) and described Blade (12) is designed that the blade (12) to be inserted through institute from the inside of rotor (4) to fix their purpose State mounting hole.

8. bladed rotor (4) as claimed in claim 1, wherein, the wall portion (18) is integrally formed.

9. bladed rotor (4) as claimed in claim 1, wherein, the wall portion (18) corresponds to single blade (12) And the net includes at least one circumferential rib (24,124), the inner casing (20,120) of the circumferential rib and stator vane stage it is interior Surface (22,122) sealing coordinates.

10. bladed rotor (4) as claimed in claim 1, wherein, the wall (16,116) is included in form the net Wall and the wall portion (18) between generally radially extending at least one articulamentum.

11. the bladed rotor of axial flow turbo-machine, including：

- blade (112)；

- the rotor structure being made up of the wall (116) for foring circular net；

- be provided with row's blade mounting hole wall (116) wall portion (118), in the upstream and/or downstream close to the wall portion Place, the wall portion (118) protrude relative to circular net,

Wherein each blade (112) includes：

- be used to for blade to be connected to platform (114) on rotor (104)；

- it is mutually contradictory and from the platform (114) along blade main shaft extension two aerodynamic surfaces (132)；

Along the main shaft of blade, the platform (114) includes：

● first layer (134), it forms a surface, for constraining liquid stream and surrounding the aerodynamic surfaces (132), and

● the second layer (136), its be located at relative to the aerodynamic surfaces (132) below the first layer (134) and by For connecting the blade；Wherein, the second layer (136) is prominent from the lower surface of the first layer (134) and including one Positioner, mechanically engaged with the elongated joining devices (126) for being contacted with the inner surface of the wall portion (118).

12. bladed rotor (104) as claimed in claim 11, wherein, the lower surface of the first layer (134) bypasses The second layer (136) and form support surface in the respective surfaces of the wall portion (118) on the platform (114).

13. the bladed rotor (104) as described in claim 11 or 12, wherein, positioner is relative to the dress The hole (138) of vaned rotor (104) circumferential orientation.

14. bladed rotor (104) as claimed in claim 11, wherein, the outer surface of the wall portion is included around every The cavity and attachment means of individual mounting hole, the cavity are used for the first layer (134) for accommodating the platform (114) of blade (112) With the second layer (136) of the platform (114) of the blade (112) that extends through the hole, the attachment means and blade (112) positioner of platform (114) and the inner surface cooperation with the wall portion (118).

15. bladed rotor (104) as claimed in claim 11, wherein, the wall portion (118) is integrally formed.

16. bladed rotor (104) as claimed in claim 11, wherein, the wall portion (118) corresponds to single blade (112) and the net includes at least one circumferential rib (24,124), the inner casing of the circumferential rib and stator vane stage (20, 120) inner surface (22,122) sealing coordinates.

17. bladed rotor (104) as claimed in claim 11, wherein, the wall (16,116) is included in form institute State at least one articulamentum generally radially extending between the wall of net and the wall portion (118).