CN202091251U - Intermediate blade of compressor with hub with diameter of phi 940 - Google Patents
Intermediate blade of compressor with hub with diameter of phi 940 Download PDFInfo
- Publication number
- CN202091251U CN202091251U CN2011201809354U CN201120180935U CN202091251U CN 202091251 U CN202091251 U CN 202091251U CN 2011201809354 U CN2011201809354 U CN 2011201809354U CN 201120180935 U CN201120180935 U CN 201120180935U CN 202091251 U CN202091251 U CN 202091251U
- Authority
- CN
- China
- Prior art keywords
- blade
- root
- working part
- section
- pairing
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
Links
Images
Landscapes
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
An intermediate blade of a compressor with a hub with the diameter of phi 940 relates to a blade and aims to resolve the problem that a molded surface of an existing intermediate blade of a compressor with a hub with the diameter of phi 940 is not smooth, and the service life of the existing intermediate blade is short. A blade working portion and a blade root are manufactured integrally from top to bottom, a molded line of the blade working portion forms a variable-cross-section twisted blade, the sectional area of the blade working portion is gradually reduced from the root to the top, and sectional geometrical data of the blade working portion from the root to the top includes that the height of a section number A-A located at the root to a section number F-F of a blade molded line portion ranges from 7.611mm to 103.869mm, axial width ranges from 64.508mm to 51.473mm, chord length ranges from 71.309mm to 71.314mm, air inlet angle ranges from 44.333 degrees to 30.672 degrees, mounting angle ranges from 63.443 degrees to 45.197 degrees, and the largest thickness of the molded line ranges from 8.341mm to 5.826mm. The intermediate blade is applied to compressors with hubs with diameters of phi 940.
Description
Technical field
The utility model relates to a kind of compressor blade.
Background technique
Because hub diameter is that the rotating speed of gas compressor of φ 940 is very high, so require blade better, aspect Security, require more strictly at aspect of performances such as strength vibrations, the each side of intergrade blade is required also further strictness.Existing hub diameter is that the gas compressor intergrade blade profile of Φ 762 designs not fairing, and efficient is low, the leaf quality instability, and efficient is low, and working life is short, has had a strong impact on the safe operation of gas compressor.
The model utility content
The purpose of this utility model is for the solution hub diameter is the not fairing of gas compressor intergrade blade profile of φ 940, the quality instability, and working life is short, influences the problem of gas compressor safe operation, and it is the gas compressor intergrade blade of φ 940 that a kind of hub diameter is provided.
The utility model is made up of blade working part and blade root, blade working part and blade root are made one from top to bottom, the molded lines of blade working part is the variable cross section twisted blade, sectional area is reduced gradually by root to top, have relatively between adjacent two sections and reverse, the geometric data in blade working part cross section from root to the top: the cross section A-A that is positioned at root to the height of the cross section F-F of vane type line part be 7.611～103.869mm, axial width is 64.508～51.473mm, chord length is 71.309～71.314mm, flow inlet angle is 44.333 °～30.672 °, established angle is 63.443 °～45.197 °, the molded lines maximum ga(u)ge is 8.341～5.826mm, trailing edge thickness is 0.489～0.346mm, and the total height of blade working part is 104.90cm.
The utility model has the advantages that: one, the utility model is in the full three dimensional design so that one dimension/standard three-dimensional/full three-dimensional is pneumatic, thermodynamic analysis calculates this intergrade blade, blade profile design fairing, make the Security and the high efficiency of this compressor blade organically combine, guaranteed energy safe and highly efficient operation under variable working condition, increased the stability of blade, improve blade efficiency, prolonged blade working life.Two, blade root is adopted the flute profile blade root, and it has the bearing capacity height, characteristics easy for installation.
Description of drawings
Fig. 1 is a plan view of the present utility model, and Fig. 2 is the left view of Fig. 1, and Fig. 3 is the plan view of Fig. 1, and Fig. 4 is the superimposed schematic representation of vane type line each cross section tomography of part, and Fig. 5 is the schematic cross-section of blade working part 1.
Embodiment
Embodiment one: present embodiment is described in conjunction with Fig. 1～Fig. 5, present embodiment is made up of blade working part 1 and blade root 2, blade working part 1 and blade root 2 are made one from top to bottom, the molded lines of blade working part 1 is the variable cross section twisted blade, sectional area is reduced gradually by root to top, have relatively between adjacent two sections and reverse, the geometric data in the cross section of blade working part 1 from root to the top: the cross section A-A that is positioned at root to the height H of the cross section F-F of vane type line part be 7.611～103.869mm, axial width B is 64.508～51.473mm, chord length b is 71.309～71.314mm, flow inlet angle α is 44.333 °～30.672 °, established angle β
yBe 63.443 °～45.197 °, molded lines maximum ga(u)ge T is 8.341～5.826mm, and trailing edge thickness δ is 0.489～0.346mm, and the total height L of blade working part 1 is 104.90cm.Design can guarantee the best stress of rotor like this, and avoids peak stress occurring in each tooth root portion and supporting plane.
Embodiment two: present embodiment is described in conjunction with Fig. 1～Fig. 4, the axial width B that the height H of the blade working part 1 of present embodiment is respectively the blade working part 1 of 26.794mm, 46.063mm, 65.331mm place correspondence respectively is: 62.283mm, 59.742mm, 57.099mm, pairing chord length b respectively is: 71.307mm, 71.306mm, 71.311mm, pairing flow inlet angle α respectively is: 41.460 °, 37.915 °, 35.403 °, and pairing established angle β
yRespectively be: 59.569 °, 55.660 °, 52.000 °, pairing molded lines maximum ga(u)ge T respectively is: 7.824mm, 7.320mm, 6.819mm, pairing trailing edge thickness δ respectively is: 0.468mm, 0.433mm, 0.404mm.Adopt the said structure parameter, not only make blade profile fairing more, can also guarantee that the contour structure size of blade meets design requirement, blade assembles easily simultaneously.Other composition and annexation are identical with embodiment one.
Embodiment three: in conjunction with Fig. 1 and Fig. 2 present embodiment is described, the blade root 2 of present embodiment is the flute profile blade root, and the axial width W of blade root 2 is 70mm, and the total height K of blade root 2 is 45.44mm, the race of tangentially packing into.This structure makes the blade wheel rim of packing into securely, and assembling is stable, safe and reliable.Other composition and annexation are identical with embodiment one or two.
Concrete parameter in each cross section such as following table:
Claims (3)
1. gas compressor intergrade blade that hub diameter is φ 940, it is made up of blade working part (1) and blade root (2), blade working part (1) and blade root (2) are made one from top to bottom, the molded lines of blade working part (1) is the variable cross section twisted blade, sectional area is reduced gradually by root to top, have relatively between adjacent two sections and reverse, it is characterized in that: the geometric data in blade working part (1) cross section from root to the top: the cross section A-A that is positioned at root to the height (H) of the cross section F-F of vane type line part be 7.611～103.869mm, axial width (B) is 64.508～51.473mm, chord length (b) is 71.309～71.314mm, flow inlet angle (α) is 44.333 °～30.672 °, established angle (β
y) be 63.443 °～45.197 °, molded lines maximum ga(u)ge (T) is 8.341～5.826mm, and trailing edge thickness (δ) is 0.489～0.346mm, and the total height (L) of blade working part (1) is 104.90cm.
2. the gas compressor intergrade blade that is φ 940 according to the described a kind of hub diameter of claim 1, it is characterized in that: the axial width (B) that the height (H) of blade working part (1) is respectively the blade working part (1) of 26.794mm, 46.063mm, 65.331mm place correspondence respectively is: 62.283mm, 59.742mm, 57.099mm, pairing chord length (b) respectively is: 71.307mm, 71.306mm, 71.311mm, pairing flow inlet angle (α) respectively is: 41.460 °, 37.915 °, 35.403 °, and pairing established angle (β
y) respectively be: 59.569 °, 55.660 °, 52.000 °, pairing molded lines maximum ga(u)ge (T) respectively is: 7.824mm, 7.320mm, 6.819mm, pairing trailing edge thickness (δ) respectively is: 0.468mm, 0.433mm, 0.404mm.
3. the gas compressor intergrade blade that is φ 940 according to claim 1 or 2 described a kind of hub diameters, it is characterized in that: described blade root (2) is the flute profile blade root, and the axial width (W) of blade root (2) is 70mm, and the total height (K) of blade root (2) is 45.44mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011201809354U CN202091251U (en) | 2011-05-31 | 2011-05-31 | Intermediate blade of compressor with hub with diameter of phi 940 |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011201809354U CN202091251U (en) | 2011-05-31 | 2011-05-31 | Intermediate blade of compressor with hub with diameter of phi 940 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202091251U true CN202091251U (en) | 2011-12-28 |
Family
ID=45366320
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011201809354U Expired - Lifetime CN202091251U (en) | 2011-05-31 | 2011-05-31 | Intermediate blade of compressor with hub with diameter of phi 940 |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202091251U (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103352871A (en) * | 2013-06-26 | 2013-10-16 | 哈尔滨汽轮机厂有限责任公司 | High-pressure middle-stage moving blade of gas compressor for gas turbine |
| RU2565090C1 (en) * | 2014-04-22 | 2015-10-20 | Открытое Акционерное Общество "Уфимское Моторостроительное Производственное Объединение" (Оао "Умпо") | Rotor shaft of low pressure compressor of turbojet engine, connection assembly of rotor shaft disks of low pressure compressor of turbojet engine |
| RU2565133C1 (en) * | 2014-04-22 | 2015-10-20 | Открытое Акционерное Общество "Уфимское Моторостроительное Производственное Объединение" (Оао "Умпо") | Rotor shaft of low pressure compressor of turbojet engine, connection assembly of rotor shaft disks of low pressure compressor of turbojet engine, spacer of connection assembly of rotor shaft disks of low pressure compressor of turbojet engine |
| RU2565092C1 (en) * | 2014-04-22 | 2015-10-20 | Открытое акционерное общество "Уфимское мотостроительное производственное объединение" (ОАО "УМПО") | Turbojet low-pressure compressor rotor impeller blade |
| RU2565091C1 (en) * | 2014-04-25 | 2015-10-20 | Открытое Акционерное Общество "Уфимское Моторостроительное Производственное Объединение" (Оао "Умпо") | Rotor impeller of lp compressor of jet turbine engine (versions) |
| RU2565113C1 (en) * | 2014-04-22 | 2015-10-20 | Открытое Акционерное Общество "Уфимское Моторостроительное Производственное Объединение" (Оао "Умпо") | Rotor shaft of low pressure compressor of turbojet engine |
| RU2565141C1 (en) * | 2014-04-22 | 2015-10-20 | Открытое Акционерное Общество "Уфимское Моторостроительное Производственное Объединение" (Оао "Умпо") | Rotor shaft of low pressure compressor of turbojet engine, connection assembly of rotor shaft disks of low pressure compressor of turbojet engine, spacer of connection assembly of rotor shaft disks of low pressure compressor of turbojet engine |
| RU2573419C2 (en) * | 2014-05-30 | 2016-01-20 | Открытое Акционерное Общество "Уфимское Моторостроительное Производственное Объединение" (Оао "Умпо") | Production of turbojet engine low-pressure compressor rotor shaft (versions) and turbojet engine low-pressure compressor rotor shaft (versions) |
| RU2581981C1 (en) * | 2014-12-23 | 2016-04-20 | Открытое Акционерное Общество "Уфимское Моторостроительное Производственное Объединение" (Оао "Умпо") | Impeller blade of rotor of compressor of low-pressure gas turbine (versions) |
| RU2596911C1 (en) * | 2015-04-10 | 2016-09-10 | Открытое Акционерное Общество "Уфимское Моторостроительное Производственное Объединение" (Оао "Умпо") | Impeller vane of turbojet engine low-pressure compressor rotor (versions) |
-
2011
- 2011-05-31 CN CN2011201809354U patent/CN202091251U/en not_active Expired - Lifetime
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103352871A (en) * | 2013-06-26 | 2013-10-16 | 哈尔滨汽轮机厂有限责任公司 | High-pressure middle-stage moving blade of gas compressor for gas turbine |
| CN103352871B (en) * | 2013-06-26 | 2015-09-16 | 哈尔滨汽轮机厂有限责任公司 | A kind of high pressure intergrade moving vane of gas turbine gas compressor |
| RU2565090C1 (en) * | 2014-04-22 | 2015-10-20 | Открытое Акционерное Общество "Уфимское Моторостроительное Производственное Объединение" (Оао "Умпо") | Rotor shaft of low pressure compressor of turbojet engine, connection assembly of rotor shaft disks of low pressure compressor of turbojet engine |
| RU2565133C1 (en) * | 2014-04-22 | 2015-10-20 | Открытое Акционерное Общество "Уфимское Моторостроительное Производственное Объединение" (Оао "Умпо") | Rotor shaft of low pressure compressor of turbojet engine, connection assembly of rotor shaft disks of low pressure compressor of turbojet engine, spacer of connection assembly of rotor shaft disks of low pressure compressor of turbojet engine |
| RU2565092C1 (en) * | 2014-04-22 | 2015-10-20 | Открытое акционерное общество "Уфимское мотостроительное производственное объединение" (ОАО "УМПО") | Turbojet low-pressure compressor rotor impeller blade |
| RU2565113C1 (en) * | 2014-04-22 | 2015-10-20 | Открытое Акционерное Общество "Уфимское Моторостроительное Производственное Объединение" (Оао "Умпо") | Rotor shaft of low pressure compressor of turbojet engine |
| RU2565141C1 (en) * | 2014-04-22 | 2015-10-20 | Открытое Акционерное Общество "Уфимское Моторостроительное Производственное Объединение" (Оао "Умпо") | Rotor shaft of low pressure compressor of turbojet engine, connection assembly of rotor shaft disks of low pressure compressor of turbojet engine, spacer of connection assembly of rotor shaft disks of low pressure compressor of turbojet engine |
| RU2565091C1 (en) * | 2014-04-25 | 2015-10-20 | Открытое Акционерное Общество "Уфимское Моторостроительное Производственное Объединение" (Оао "Умпо") | Rotor impeller of lp compressor of jet turbine engine (versions) |
| RU2573419C2 (en) * | 2014-05-30 | 2016-01-20 | Открытое Акционерное Общество "Уфимское Моторостроительное Производственное Объединение" (Оао "Умпо") | Production of turbojet engine low-pressure compressor rotor shaft (versions) and turbojet engine low-pressure compressor rotor shaft (versions) |
| RU2581981C1 (en) * | 2014-12-23 | 2016-04-20 | Открытое Акционерное Общество "Уфимское Моторостроительное Производственное Объединение" (Оао "Умпо") | Impeller blade of rotor of compressor of low-pressure gas turbine (versions) |
| RU2596911C1 (en) * | 2015-04-10 | 2016-09-10 | Открытое Акционерное Общество "Уфимское Моторостроительное Производственное Объединение" (Оао "Умпо") | Impeller vane of turbojet engine low-pressure compressor rotor (versions) |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN202091251U (en) | Intermediate blade of compressor with hub with diameter of phi 940 | |
| CN102168687B (en) | Compressor first-stage blade with hub diameter of phi 762 | |
| CN202176549U (en) | Secondary first-stage blade for air compressor of high power combustion gas turbine | |
| CN203756593U (en) | High-efficient centrifugal wind wheel | |
| CN201496290U (en) | Low consumption high efficiency automatable axial flow cooling fan | |
| CN102588338A (en) | Axial fan | |
| CN202176550U (en) | Intermediate stage guide vane of compressor for large-power gas turbine | |
| CN202065241U (en) | First-stage blade of air compressor with hub diameter of phi 762 | |
| CN203384065U (en) | Multi-vane fan | |
| CN202091253U (en) | Intermediate blade of gas compressor with hub diameter of [phi] 658 | |
| CN105257596A (en) | Bird wing type high-pressure axial flow fan vane and counter rotating axial flow fan comprising same | |
| CN202091254U (en) | Primary blade of gas compressor with hub diameter of [phi] 940 | |
| CN202048023U (en) | Primary blade of large-sized high-rotation-speed air compressor | |
| CN202065242U (en) | Intermediate stage blade of air compressor with hub diameter of Phi 762 | |
| CN202441647U (en) | Impeller and centrifugal compressor comprising same | |
| CN202091249U (en) | Intermediate-stage blade of gas compressor with hub diameter of Phi 564mm | |
| CN201103419Y (en) | Second last blade of macrotype supercritical air cooling turbine | |
| CN203161649U (en) | Variable-installation-angle axial fan | |
| CN205714938U (en) | Multistage turbine vacuum pump impeller | |
| CN202065243U (en) | Air compressor first-stage blade with hub diameter of phi 616 | |
| CN211008775U (en) | Moving blade with long and short wings and rotor | |
| CN202065239U (en) | Interstage blade of air compressor with hub diameter of phi 616 | |
| CN202073835U (en) | First-stage blade of compressor with phi564 hub diameter | |
| CN201225325Y (en) | Plastic axial cooling fan | |
| CN201475001U (en) | Low-noise automobile axial-flow cooling fan |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term |
Granted publication date: 20111228 |
|
| CX01 | Expiry of patent term |