CN102454430A - High pressure nozzle set for turbomachine - Google Patents
High pressure nozzle set for turbomachine Download PDFInfo
- Publication number
- CN102454430A CN102454430A CN2010105282097A CN201010528209A CN102454430A CN 102454430 A CN102454430 A CN 102454430A CN 2010105282097 A CN2010105282097 A CN 2010105282097A CN 201010528209 A CN201010528209 A CN 201010528209A CN 102454430 A CN102454430 A CN 102454430A
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- China
- Prior art keywords
- high pressure
- pressure nozzle
- nozzle set
- blade
- blades
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- 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.)
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Abstract
The invention provides a morel durable high pressure nozzle set for a turbomachine, comprising a nozzle set main body provided with a ring groove, wherein uniformly distributed blades instead of spacing blocks are arranged in the ring groove. The high pressure nozzle set replaces the original spacing blocks with blades such that the airflow is more uniform and stable. The high pressure nozzle set also reduces damages and cracks, which are caused by the backlash of the airflow, for the first row of blades at the double-velocity stage. The high pressure nozzle set can raise the efficiency.
Description
Technical field
The present invention relates to a kind of high pressure nozzle group of turbine engine, especially a kind of blade nozzle.
Background technique
Turbine engine high pressure nozzle group is used for the supercharging of turbine engine steam, forms gas compression.
For a long time; The turbine engine high pressure nozzle group of blade type is following structure; Comprise the nozzle sets body that is provided with annular groove; And evenly being arranged on a plurality of spacer blocks in the said annular groove, said spacer block is connected between two cell walls of annular groove, is one group of blade that a plurality of blades are uniformly distributed with formation between every two adjacent spacer blocks.
The main effect of spacer block is to strengthen the intensity and the rigidity of whole assembly in the said structure; Although the plate face tilt direction with spacer block is consistent with blade blade face rotation direction as far as possible, because spacer block shape and blade shape differ greatly, near the air-flow it is inhomogeneous; Cause eddy current easily; Cause the damage to blade, near the blade the spacer block fractures easily, influences proper functioning.
Summary of the invention
In order to overcome the deficiency of existing turbine engine high pressure nozzle group blade easy damaged, technical problem to be solved by this invention provides a kind of more durable turbine engine high pressure nozzle group.
The technical solution adopted for the present invention to solve the technical problems is: turbine engine high pressure nozzle group, comprise the nozzle sets body that is provided with annular groove, and all be the blade that is uniformly distributed with in the said annular groove.
The invention has the beneficial effects as follows: with the original spacer block of blade replacement, make air-flow more even, stable, reduce eddy current and produce; Reduced the injury of the recoil of air-flow to the velocity-compounded stage first row blade; Fracture, and can raise the efficiency, the working life of high pressure nozzle group improved.
Description of drawings
Fig. 1 is the schematic representation of existing turbine engine high pressure nozzle group.
Fig. 2 is near the schematic representation that produces eddy current the existing turbine engine dividing plate.
Fig. 3 is the schematic representation of turbine engine high pressure nozzle group of the present invention.
Be labeled as 1-nozzle sets body, 2-spacer block, 3-blade, 4-annular groove among the figure.
Black region is for being prone to produce eddy region among Fig. 2.
Embodiment
Below in conjunction with accompanying drawing the present invention is further specified.
With reference to figure 1, Fig. 2, as shown in Figure 3, turbine engine high pressure nozzle group of the present invention comprises the nozzle sets body 1 that is provided with annular groove 4; But in the said annular groove 4 spacer block 2 is set no longer, mounting blades 3 in the position of former installation spacer block 2, all are a plurality of blades 3 that are uniformly distributed with in the annular groove 4 promptly; Make air-flow more even, stable, reduced the eddy current generation, reduced the injury of the recoil of air-flow the velocity-compounded stage first row blade; Fracture, and can raise the efficiency, the working life of high pressure nozzle group improved.
Claims (1)
1. turbine engine high pressure nozzle group comprises the nozzle sets body (1) that is provided with annular groove (4), it is characterized in that: in the said annular groove (4) all is the blade (3) that is uniformly distributed with.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010105282097A CN102454430A (en) | 2010-11-02 | 2010-11-02 | High pressure nozzle set for turbomachine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010105282097A CN102454430A (en) | 2010-11-02 | 2010-11-02 | High pressure nozzle set for turbomachine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102454430A true CN102454430A (en) | 2012-05-16 |
Family
ID=46038051
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2010105282097A Pending CN102454430A (en) | 2010-11-02 | 2010-11-02 | High pressure nozzle set for turbomachine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102454430A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR101625794B1 (en) * | 2015-04-06 | 2016-05-30 | 두산중공업 주식회사 | Nozzle box for turbine |
-
2010
- 2010-11-02 CN CN2010105282097A patent/CN102454430A/en active Pending
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR101625794B1 (en) * | 2015-04-06 | 2016-05-30 | 두산중공업 주식회사 | Nozzle box for turbine |
| EP3085898A1 (en) * | 2015-04-06 | 2016-10-26 | Doosan Heavy Industries & Construction Co., Ltd. | Turbine nozzle box |
| US10190427B2 (en) | 2015-04-06 | 2019-01-29 | DOOSAN Heavy Industries Construction Co., LTD | Turbine nozzle box |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20120516 |