CN204941609U - A kind of rotor blade - Google Patents
A kind of rotor blade Download PDFInfo
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- CN204941609U CN204941609U CN201520719067.0U CN201520719067U CN204941609U CN 204941609 U CN204941609 U CN 204941609U CN 201520719067 U CN201520719067 U CN 201520719067U CN 204941609 U CN204941609 U CN 204941609U
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- rotor blade
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Abstract
The utility model discloses a kind of rotor blade, belong to engine rotor blade design field.Described rotor blade comprises blade (1) and tenon (3), described tenon (3) is metallic material, slot in one end, one end of described blade (1) is inserted in the groove of described tenon (3), and being fixedly connected with described tenon (3), the other end of described tenon (3) is arranged to be installed to the structure on turbine engine disk.Blade tenon partial design is Structural Hardware by the utility model, and blade part is still composite material, forms complete blade after connecting.Adopt this design can simplify the design difficulty of composite portions, strengthen the reliability of tongue portion simultaneously, improve the abrasive resistance of tongue portion.
Description
Technical field
The utility model belongs to Aeroengine Design field, is specifically related to a kind of composite material rotor blade with metal tenon.
Background technique
The working condition of turbine rotor blade plays decisive role to the usability of aeroengine and operational safety.This is because turbine rotor blade works under high-temperature fuel gas surrounds, the effect of blade self centrifugal force, aerodynamic force, thermal stress and vibration stress etc. when it not only bears turbine rotor High Rotation Speed, also will bear the washing away of high-temperature fuel gas, be oxidized and corrosive action, be the part that in aeroengine, operating conditions is the most severe.
In prior art, adopt composite material to manufacture turbine engine rotor blade, considerable weight loss effect can be obtained.Composite material blade usually adopts the different prepreg overlay of shape to solidify and forms.Root is used for connecting with other parts, but because its load of bearing is comparatively complicated, its thickness is greater than other positions of blade usually, therefore needs additionally stacking tens prepreg overlays.So many laying utilization is manually carried out stacking, not only adds workload, if deviation appears in stacked position, the tenon shape after solidifying also can be caused to be difficult to meet size requirement, cause blade working penalty, and then the loss of aggravation tenon, reduce functional reliability.
Model utility content
In order to solve the problem, overcome existing composite material rotor blade tenon Lay up design complicated, the drawback that operability is low, the utility model provides a kind of rotor blade, be Structural Hardware by blade tenon partial design, blade part is still composite material, forms complete blade after connecting.Adopt this design can simplify the design difficulty of composite portions, strengthen the reliability of tongue portion simultaneously, improve the abrasive resistance of tongue portion.Concrete, described rotor blade comprises: blade and tenon, and described tenon is metallic material, slot in one end, one end of described blade is inserted in the groove of described tenon, and is fixedly connected with described tenon, and the other end of described tenon is arranged to be installed to the structure on turbine engine disk.
Preferably, described blade and tenon pass through rivet interlacement.
, described blade is composite material in such scheme preferably, adopt prepreg solidifying, and the position that itself and tenon are riveted on described blade is provided with through hole.
The utility model has the advantage of, composite material blade part adopts prepreg solidifying, and original leaf root part does not need to carry out Lay up design specially, thus simplifies work flow.Metal tenon adopts cutting shaping, and processing speed is fast, and formed precision is high, and has higher antiwear property, can effectively extend the root of blade life-span.
Accompanying drawing explanation
Fig. 1 is the structural representation of the preferred embodiment according to the utility model rotor blade.
Wherein, 1-blade; 2-tenon; 3-rivet.
Embodiment
The object implemented for making the utility model, technological scheme and advantage clearly, below in conjunction with the accompanying drawing in the utility model embodiment, are further described in more detail the technological scheme in the utility model embodiment.In the accompanying drawings, same or similar label represents same or similar element or has element that is identical or similar functions from start to finish.Described embodiment is the utility model part embodiment, instead of whole embodiments.Be exemplary below by the embodiment be described with reference to the drawings, be intended to for explaining the utility model, and can not be interpreted as restriction of the present utility model.Based on the embodiment in the utility model, those of ordinary skill in the art are not making the every other embodiment obtained under creative work prerequisite, all belong to the scope of the utility model protection.Below in conjunction with accompanying drawing, embodiment of the present utility model is described in detail.
In description of the present utility model, it will be appreciated that, term " " center ", " longitudinal direction ", " transverse direction ", " front ", " afterwards ", " left side ", " right side ", " vertically ", " level ", " top ", " end " " interior ", orientation or the position relationship of the instruction such as " outward " are based on orientation shown in the drawings or position relationship, only the utility model and simplified characterization for convenience of description, instead of indicate or imply that the device of indication or element must have specific orientation, with specific azimuth configuration and operation, therefore the restriction to the utility model protection domain can not be interpreted as.
Fig. 1 gives the concrete structure of the utility model rotor blade, mainly comprise blade 1 and tenon 3 two-part, one end fluting of tenon 3, one end of groove size and blade 1 matches, one end of blade 1 can be stretched in above-mentioned groove just, afterwards, blade 1 is fixed in described groove, means of fixation is varied, such as, by the Placement such as rivet, bolt, or by the Placement such as interference fit, clamping, in the present embodiment, in order to make blade have high strength, high reliability, rivet is adopted to connect.
For this reason, need when tenon 3 and blade 1 preprocessing, leaving is suitable attachment hole, such as, add man-hour at tenon, in corresponding position, the both sides perforate of groove, be convenient to riveted joint, equally, add man-hour at blade 1, stretch into the one end in the groove of tenon 3 at it, the position corresponding with slotted eye has through hole.Tenon 3 through the hole of the hole of groove one end of tenon 3, the through hole of blade 1, the groove the other end of tenon 3, is fixedly connected with blade 1 by rivet 2 successively.
Should be understood that, described blade 1 adopts traditional manufacture method, selects composite material, adopts prepreg solidifying; And tenon 3 adopts metallic material to make, shaping by cutting mode, processing speed is fast, and formed precision is high, and has higher antiwear property, can effectively extend the root of blade life-span.
The root of the blade 1 that composite material of the present utility model makes can insert in the tenon 3 upper end open groove that metallic material makes, and shape can realize good fit with tenon.At composite material blade relevant position processing open pore, with rivet 2, composite material blade and metal tenon are riveted, complete blade can be obtained.
It should be noted that in addition, for rotor blade is installed on turbine engine disk, one end away from blade of described tenon 3 is arranged to be installed to the structure on turbine engine disk, its concrete shape designs according to turbine engine disk shape, or traditionally root of blade designs, the root of described traditional blades, i.e. one end of blade and turbine engine disk joint.
Finally it is to be noted: above embodiment only in order to the technical solution of the utility model to be described, is not intended to limit.Although be described in detail the utility model with reference to previous embodiment, those of ordinary skill in the art is to be understood that: it still can be modified to the technological scheme described in foregoing embodiments, or carries out equivalent replacement to wherein portion of techniques feature; And these amendments or replacement, do not make the essence of appropriate technical solution depart from the spirit and scope of each embodiment's technological scheme of the utility model.
Claims (3)
1. a rotor blade, it is characterized in that: comprise blade (1) and tenon (3), described tenon (3) is metallic material, slot in one end, one end of described blade (1) is inserted in the groove of described tenon (3), and being fixedly connected with described tenon (3), the other end of described tenon (3) is arranged to be installed to the structure on turbine engine disk.
2. rotor blade as claimed in claim 1, is characterized in that: described blade (1) is connected by rivet (2) with tenon (3).
3. rotor blade as claimed in claim 2, is characterized in that: described blade (1) is composite material, adopts prepreg solidifying, and is provided with through hole at described blade (1) position that above itself and tenon (3) are riveted.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520719067.0U CN204941609U (en) | 2015-09-16 | 2015-09-16 | A kind of rotor blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520719067.0U CN204941609U (en) | 2015-09-16 | 2015-09-16 | A kind of rotor blade |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204941609U true CN204941609U (en) | 2016-01-06 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520719067.0U Active CN204941609U (en) | 2015-09-16 | 2015-09-16 | A kind of rotor blade |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204941609U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110107362A (en) * | 2019-05-31 | 2019-08-09 | 南京赛达机械制造有限公司 | High-strength corrosion-resisting steam turbine fastening type movable vane piece |
-
2015
- 2015-09-16 CN CN201520719067.0U patent/CN204941609U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110107362A (en) * | 2019-05-31 | 2019-08-09 | 南京赛达机械制造有限公司 | High-strength corrosion-resisting steam turbine fastening type movable vane piece |
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| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |