CN204436483U - A kind of turbine blade-tip gap ACTIVE CONTROL mechanism - Google Patents
A kind of turbine blade-tip gap ACTIVE CONTROL mechanism Download PDFInfo
- Publication number
- CN204436483U CN204436483U CN201520079388.9U CN201520079388U CN204436483U CN 204436483 U CN204436483 U CN 204436483U CN 201520079388 U CN201520079388 U CN 201520079388U CN 204436483 U CN204436483 U CN 204436483U
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- Prior art keywords
- gap
- ring
- casing
- turbine blade
- turbine
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- Expired - Fee Related
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Abstract
A kind of turbine blade-tip gap ACTIVE CONTROL mechanism, relates to aero engine turbine blades.The gas leakage that can reduce blade point place is provided, increases a kind of turbine blade-tip gap ACTIVE CONTROL mechanism of turbine efficiency.Be provided with retaining ring, feeding bolt, gap control ring, make rotating ring, casing, turbine blade, rocking arm; Retaining ring is arranged on the periphery of casing, the feeding bolt major part flank of tooth is located on retaining ring, to ensure the firm of structure, the end of feeding bolt is connected with gap control ring, gap control ring is embedded in the inner side of casing, leave gap between the end of gap control ring and the inner side of casing, do to leave gap between rotating ring and casing, to be installed on casing as rotating ring and to be connected with feeding bolt by rocking arm.Structure control logic is simple, highly sensitive, fast response time.When turbine inlet temperature changes, by rotarily driving rocking arm as rotating ring, the amount of feed of feeding bolt being changed, driving the motion of gap control ring, changing turbine blade-tip gap.
Description
Technical field
The utility model relates to aero engine turbine blades, especially relates to a kind of turbine blade-tip gap ACTIVE CONTROL mechanism.
Background technique
The one of the main reasons that civil engine is changed is that turbine part decline causes turbine exhaust gas temperature to exceed given nargin and oil consumption rate increases, and the increase of turbine blade-tip gap is the principal element of turbine efficiency decay.Less turbine blade-tip gap can reduce the gas leakage at blade point place, increases turbine efficiency, makes to start function to meet performance and power target with less fuel consume and lower rotor inlet temperature.If turbine blade-tip gap is too small, blade tip and turbine outer ring can be caused to touch mill when engine condition changes fast.Therefore, turbine blade-tip gap controls engine high-efficiency, safety and reliably work most important.
Turbine blade-tip gap active control technology (hereinafter referred to as active clearance control technique) is an important technique measure reducing engine oil consumption rate by the change controlling turbine blade-tip gap, improve reliability and increase the service life, also there is larger contribution to the discharge of decreasing pollution thing simultaneously, therefore, this technology is considered to develop one of core technology that advanced civilian large Bypass Ratio Turbofan Engine must grasp.
Summary of the invention
The purpose of this utility model is to provide the gas leakage that can reduce blade point place, increases a kind of turbine blade-tip gap ACTIVE CONTROL mechanism of turbine efficiency.
The utility model is provided with retaining ring, feeding bolt, gap control ring, makes rotating ring, casing, turbine blade, rocking arm;
Retaining ring is arranged on the periphery of casing, the feeding bolt major part flank of tooth is located on retaining ring, to ensure the firm of structure, the end of feeding bolt is connected with gap control ring, gap control ring is embedded in the inner side of casing, leave gap between the end of gap control ring and the inner side of casing, do to leave gap between rotating ring and casing, to be installed on casing as rotating ring and to be connected with feeding bolt by rocking arm.
Retaining ring of the present utility model, make rotating ring, casing and rocking arm circumference and be distributed in outside turbine casing, be connected with the gap control ring be positioned at inside turbine casing by feeding bolt.
Compared with the prior art, the utility model tool has the following advantages:
The utility model structure control logic is simple, highly sensitive, fast response time.When turbine inlet temperature changes, by rotarily driving rocking arm as rotating ring, the amount of feed of feeding bolt being changed, driving the motion of gap control ring, changing turbine blade-tip gap.
Accompanying drawing explanation
Fig. 1 is the schematic appearance of the utility model embodiment.
Fig. 2 is the internal structure schematic diagram of the utility model embodiment.
Embodiment
See Fig. 1 and 2, the present embodiment is provided with retaining ring 1-1, feeding bolt 1-2, gap control ring 1-3, makes rotating ring 1-4, casing 1-5, turbine blade 1-6, rocking arm 1-7.
Retaining ring 1-1 is arranged on the periphery of casing 1-5, the feeding bolt 1-2 major part flank of tooth is located on retaining ring 1-1, to ensure the firm of structure, the end of feeding bolt 1-2 is connected with gap control ring 1-3, gap control ring 1-3 is embedded in the inner side of casing 1-5, leave clearance C between the end of gap control ring 1-3 and the inner side of casing 1-5, do to leave gap A between rotating ring 1-4 and casing 1-5, make rotating ring 1-4 and to be installed on casing 1-5 and to be connected with feeding bolt 1-2 by rocking arm 1-7.
When turbine inlet temperature reduces, the expansion of turbine blade 1-6 reduces, tip clearance B becomes large, make rotating ring 1-4 clockwise rotation, drive rocking arm 1-7; rocking arm 1-7 drives feeding bolt 1-2 to produce feed movement, makes gap control ring 1-3 near turbine blade 1-6, ensures that turbine blade-tip gap B reduces.
When turbine raises when turbine inlet temperature, the expansion of turbine blade 1-6 increases, and makes rotating ring 1-4 counter-clockwise rotary motion, drives rocking arm 1-7, makes gap control ring 1-3 away from turbine blade 1-6, ensures that turbine blade-tip gap B maintains in stable margin range.
Claims (1)
1. a turbine blade-tip gap ACTIVE CONTROL mechanism, is characterized in that being provided with retaining ring, feeding bolt, gap control ring, making rotating ring, casing, turbine blade, rocking arm;
Retaining ring is arranged on the periphery of casing, the feeding bolt major part flank of tooth is located on retaining ring, to ensure the firm of structure, the end of feeding bolt is connected with gap control ring, gap control ring is embedded in the inner side of casing, leave gap between the end of gap control ring and the inner side of casing, do to leave gap between rotating ring and casing, to be installed on casing as rotating ring and to be connected with feeding bolt by rocking arm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520079388.9U CN204436483U (en) | 2015-02-04 | 2015-02-04 | A kind of turbine blade-tip gap ACTIVE CONTROL mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520079388.9U CN204436483U (en) | 2015-02-04 | 2015-02-04 | A kind of turbine blade-tip gap ACTIVE CONTROL mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204436483U true CN204436483U (en) | 2015-07-01 |
Family
ID=53604361
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520079388.9U Expired - Fee Related CN204436483U (en) | 2015-02-04 | 2015-02-04 | A kind of turbine blade-tip gap ACTIVE CONTROL mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204436483U (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105840549A (en) * | 2016-03-30 | 2016-08-10 | 中国科学院工程热物理研究所 | Mechanism for active control over blade top gap and case shape of air compressor within full working condition range |
| CN108019242A (en) * | 2017-12-15 | 2018-05-11 | 北京航空航天大学 | Aero-engine tip clearance active control device based on shape-memory alloy wire |
| CN110925232A (en) * | 2019-12-03 | 2020-03-27 | 北京航空航天大学 | Blade tip clearance monitoring and control device |
| CN113062781A (en) * | 2021-05-06 | 2021-07-02 | 中国航发湖南动力机械研究所 | Centering and positioning structure for CMC gas turbine outer ring |
| CN114294068A (en) * | 2021-10-20 | 2022-04-08 | 中国航发四川燃气涡轮研究院 | Mounting structure and turbine engine of apex clearance sensor on double-deck quick-witted casket |
| CN114483206A (en) * | 2021-12-29 | 2022-05-13 | 西安鑫垚陶瓷复合材料有限公司 | Floating ceramic matrix composite turbine outer ring and assembling structure and method of outer ring and casing |
| CN114718659A (en) * | 2022-03-24 | 2022-07-08 | 西北工业大学 | Turbine blade tip clearance flow control method for coupling radial ribs and circumferential grooves |
-
2015
- 2015-02-04 CN CN201520079388.9U patent/CN204436483U/en not_active Expired - Fee Related
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105840549A (en) * | 2016-03-30 | 2016-08-10 | 中国科学院工程热物理研究所 | Mechanism for active control over blade top gap and case shape of air compressor within full working condition range |
| CN108019242A (en) * | 2017-12-15 | 2018-05-11 | 北京航空航天大学 | Aero-engine tip clearance active control device based on shape-memory alloy wire |
| CN110925232A (en) * | 2019-12-03 | 2020-03-27 | 北京航空航天大学 | Blade tip clearance monitoring and control device |
| CN113062781A (en) * | 2021-05-06 | 2021-07-02 | 中国航发湖南动力机械研究所 | Centering and positioning structure for CMC gas turbine outer ring |
| CN114294068A (en) * | 2021-10-20 | 2022-04-08 | 中国航发四川燃气涡轮研究院 | Mounting structure and turbine engine of apex clearance sensor on double-deck quick-witted casket |
| CN114294068B (en) * | 2021-10-20 | 2023-06-30 | 中国航发四川燃气涡轮研究院 | Mounting structure of blade tip clearance sensor on double-layer casing and turbine engine |
| CN114483206A (en) * | 2021-12-29 | 2022-05-13 | 西安鑫垚陶瓷复合材料有限公司 | Floating ceramic matrix composite turbine outer ring and assembling structure and method of outer ring and casing |
| CN114718659A (en) * | 2022-03-24 | 2022-07-08 | 西北工业大学 | Turbine blade tip clearance flow control method for coupling radial ribs and circumferential grooves |
| CN114718659B (en) * | 2022-03-24 | 2023-05-23 | 西北工业大学 | Turbine blade tip clearance flow control method coupling radial ribs and circumferential grooves |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20150701 Termination date: 20180204 |