CN112780357A - Turbine blade with film hole cooling structure based on eddy effect - Google Patents
Turbine blade with film hole cooling structure based on eddy effect Download PDFInfo
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- CN112780357A CN112780357A CN202110320601.0A CN202110320601A CN112780357A CN 112780357 A CN112780357 A CN 112780357A CN 202110320601 A CN202110320601 A CN 202110320601A CN 112780357 A CN112780357 A CN 112780357A
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- film hole
- turbine blade
- cooling structure
- vortex effect
- vortex
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/186—Film cooling
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
A turbine blade with a film hole cooling structure based on a vortex effect. The turbine blade comprises a turbine blade body and at least one film hole cooling structure which is arranged inside the turbine blade body and is based on the vortex effect; the air film hole cooling structure comprises an air inlet duct, a hot air duct, a cold air duct and a vortex chamber; the turbine blade with the film hole cooling structure based on the vortex effect has the following beneficial effects: the air-conditioning device can separate cold air flow with relatively lower temperature, provides cooling air with lower temperature aiming at the wall surface with relatively higher cooling performance requirement, can effectively improve the quality of the cold air, improves the air film cooling effect, relieves the temperature level of hot end parts such as turbine blades and the like, and improves the overall efficiency of the aircraft engine.
Description
Technical Field
The invention belongs to the technical field of cooling and heat transfer of turbine blades of aero-engines, and particularly relates to a turbine blade with an air film hole cooling structure based on a vortex effect.
Background
The improvement of the thrust of the aeroengine depends on the improvement of the total temperature T3 before the turbine to a great extent, and according to related research results, the improvement of the thrust of the 55K aeroengine by the total temperature T3 before the turbine can be improved by about 10 percent under the condition that the size of the aeroengine is not changed. At present, the boost ratio of an aircraft engine compressor with a thrust-weight ratio of 10 reaches 30, the temperature of gas at the inlet of a turbine is close to 2000K and far exceeds the limit temperature of a metal material, so that the turbine blade needs to be effectively cooled to ensure that the turbine blade can normally and reliably work for a long time due to the increase of the limit temperature of the metal material.
The basic principle of air film cooling is that small holes are formed in the surface of a turbine blade, cold air is sprayed into main air flow along a certain direction, and jet flow is bent and covers the surface of a high-temperature part under the action of pressure and friction force of the main air flow, so that a cold air film with a lower temperature is formed to separate the turbine blade from high-temperature gas and take away part of the high-temperature gas and radiation heat to the wall surface, and the turbine blade is protected.
The vortex tube has the working principle that high-pressure gas enters a vortex tube nozzle, expands in the nozzle and accelerates to the speed of sound, and then is injected into a vortex chamber from the tangential direction to form free vortex. The greater the rotational angular velocity of the free vortex is near the center, the different angular velocities create friction between the layers of the free vortex. The air flow speed of the central part is the largest, the friction result is that the energy is transferred to the air flow with lower angular velocity of the outer layer, the air flow of the central part loses the energy to obtain the cold air flow required by refrigeration, and the air flow of the outer layer part forms the hot air flow.
Disclosure of Invention
In order to solve the above problems, an object of the present invention is to provide a turbine blade with a film hole cooling structure based on a vortex effect.
In order to achieve the above object, the present invention provides a turbine blade with a film hole cooling structure based on vortex effect, which comprises a turbine blade body and at least one film hole cooling structure based on vortex effect, wherein the film hole cooling structure based on vortex effect is arranged inside the turbine blade body; the film hole cooling structure based on the vortex effect comprises an air inlet duct, a hot air duct, a cold air duct and a vortex chamber; one end of the air inlet pore passage is connected with one side surface of the vortex chamber, and the other end of the air inlet pore passage is connected with an inner cooling channel in the turbine blade body; one end of the hot air duct and one end of the cold air duct are respectively connected to two opposite side surfaces of the vortex chamber, the other end of the cold air duct penetrates through the outer side surface of the turbine blade body and then is connected with one air film hole, and the other end of the hot air duct penetrates through the outer side surface of the turbine blade body and then is connected with the other air film hole or is directly connected with an inner cooling channel in the turbine blade body.
The cross section of the air film hole is circular, oval or fan-shaped, the air film hole outlet connected with the cold air duct is close to the wall surface which is positioned at the downstream and has relatively high cooling performance requirement, and the air film hole outlet connected with the hot air duct is close to the wall surface which is positioned at the downstream and has relatively low cooling performance requirement.
When the film hole cooling structure based on the vortex effect is arranged, the specific position of the film hole cooling structure is determined according to the cooling requirement of the turbine blade; when a plurality of film hole cooling structures based on the vortex effect are arranged, the film hole cooling structures based on the vortex effect are arranged on the turbine blade body in a staggered or arc-shaped arrangement mode at intervals along the curvature of the turbine blade body.
The turbine blade with the film hole cooling structure based on the vortex effect has the following beneficial effects: the air conditioner can separate cold air flow with relatively lower temperature, provides cooling gas with lower temperature aiming at the wall surface with relatively higher cooling performance requirement, can effectively improve the quality of the cold air, improves the air film cooling effect, relieves the temperature level of hot end parts such as turbine blades and the like, and improves the overall efficiency of the aero-engine.
Drawings
FIG. 1 is a cross-sectional view of a turbine blade with a film hole cooling structure based on the vortex effect according to embodiment 1 of the present invention.
FIG. 2 is a cross-sectional view of a turbine blade with a film hole cooling structure based on the vortex effect according to embodiment 2 of the present invention.
Detailed Description
The invention is described in detail below with reference to the figures and specific embodiments.
Example 1
As shown in FIG. 1, the turbine blade with the film hole cooling structure based on the vortex effect provided by the present embodiment comprises a turbine blade body 5 and at least one film hole cooling structure based on the vortex effect, which is arranged inside the turbine blade body 5; the film hole cooling structure based on the vortex effect comprises an air inlet duct 1, a hot air duct 2, a cold air duct 3 and a vortex chamber 4; wherein, one end of the air inlet duct 1 is connected with one side surface of the vortex chamber 4, and the other end is connected with an inner cooling channel in the turbine blade body 5; one end of the hot air duct 2 and one end of the cold air duct 3 are respectively connected with two opposite side surfaces of the vortex chamber 4, and the other ends of the hot air duct and the cold air duct respectively penetrate through the outer side surface of the turbine blade body 5 and then are connected with a film hole.
The section of the air film hole is circular, oval or fan-shaped, the air film hole outlet connected with the cold air duct 3 is close to the wall surface which is positioned at the downstream and has relatively high cooling performance requirement, and the air film hole outlet connected with the hot air duct 2 is close to the wall surface which is positioned at the downstream and has relatively low cooling performance requirement.
When the film hole cooling structure based on the vortex effect is arranged, the specific position of the film hole cooling structure is determined according to the cooling requirement of the turbine blade; when a plurality of film hole cooling structures based on the vortex effect are arranged, the film hole cooling structures based on the vortex effect are arranged on the turbine blade body 5 at intervals in a staggered mode or in an arc line arrangement mode along the curvature of the turbine blade body 5.
The working principle of the turbine blade with the film hole cooling structure based on the vortex effect provided by the embodiment is explained as follows:
the high-pressure air flow from the inner cooling channel firstly enters the vortex chamber 4 through the air inlet duct 1. The high-pressure airflow will generate vortex effect in the vortex chamber 4 and is separated into cold airflow and hot airflow; then the cold air flow is led into the air film hole connected with the cold air duct 3 through the cold air duct, and finally is ejected out from the air film hole outlet to form effective air film protection for the wall surface which is positioned at the downstream of the air film hole and has relatively higher cooling performance requirement, and the hot air flow is led into the air film hole connected with the hot air duct 2 through the hot air duct, and finally is ejected out from the air film hole outlet to form effective air film protection for the wall surface which is positioned at the downstream of the air film hole and has relatively lower cooling performance requirement.
Example 2:
as shown in fig. 2, the turbine blade with the film hole cooling structure based on the vortex effect provided in the present embodiment has the same basic structure as the turbine blade with the film hole cooling structure based on the vortex effect provided in embodiment 1, except that the other end of the hot gas duct 2 is connected to an internal cooling passage in the turbine blade body 5.
The working principle of the turbine blade with the film hole cooling structure based on the vortex effect provided by the embodiment is explained as follows:
the high-pressure air flow from the inner cooling channel firstly enters the vortex chamber 4 through the air inlet duct 1. The high-pressure airflow will generate vortex effect in the vortex chamber 4 and is separated into cold airflow and hot airflow; then the cold air flow is led into the connected air film hole through the cold air duct 3, and finally is ejected out from the air film hole outlet to form effective air film protection for the wall surface which is positioned at the downstream of the air film hole and has relatively higher cooling performance requirement, and the hot air flow is led into the connected inner cooling channel through the hot air duct 2 to carry out inner cooling on the turbine blade body 5.
Claims (3)
1. A turbine blade with a film hole cooling structure based on vortex effect is characterized in that: the turbine blade with the film hole cooling structure based on the vortex effect comprises a turbine blade body (5) and at least one film hole cooling structure based on the vortex effect, wherein the film hole cooling structure based on the vortex effect is arranged inside the turbine blade body (5); the film hole cooling structure based on the vortex effect comprises an air inlet duct (1), a hot air duct (2), a cold air duct (3) and a vortex chamber (4); wherein one end of the air inlet duct (1) is connected with one side surface of the vortex chamber (4), and the other end is connected with an inner cooling channel in the turbine blade body (5); one end of the hot air duct (2) and one end of the cold air duct (3) are respectively connected to two opposite side surfaces of the vortex chamber (4), the other end of the cold air duct (3) penetrates through the outer side surface of the turbine blade body (5) and then is connected with one air film hole, and the other end of the hot air duct (2) penetrates through the outer side surface of the turbine blade body (5) and then is connected with the other air film hole or is directly connected with an inner cooling channel in the turbine blade body (5).
2. The turbine blade with a film hole cooling configuration based on vortex effect of claim 1, wherein: the section of the air film hole is circular, oval or fan-shaped, the air film hole outlet connected with the cold air duct (3) is close to the wall surface which is positioned at the downstream and has relatively high cooling performance requirement, and the air film hole outlet connected with the hot air duct (2) is close to the wall surface which is positioned at the downstream and has relatively low cooling performance requirement.
3. The turbine blade with a film hole cooling configuration based on vortex effect of claim 1, wherein: when the film hole cooling structure based on the vortex effect is arranged, the specific position of the film hole cooling structure is determined according to the cooling requirement of the turbine blade; when a plurality of film hole cooling structures based on the vortex effect are arranged, the film hole cooling structures based on the vortex effect are arranged on the turbine blade body (5) in a staggered mode or in an interval mode along the curved arc line of the turbine blade body (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110320601.0A CN112780357A (en) | 2021-03-25 | 2021-03-25 | Turbine blade with film hole cooling structure based on eddy effect |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110320601.0A CN112780357A (en) | 2021-03-25 | 2021-03-25 | Turbine blade with film hole cooling structure based on eddy effect |
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| CN112780357A true CN112780357A (en) | 2021-05-11 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202110320601.0A Pending CN112780357A (en) | 2021-03-25 | 2021-03-25 | Turbine blade with film hole cooling structure based on eddy effect |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN87101766A (en) * | 1986-02-04 | 1987-10-07 | 沃特·希伯特森 | The cooling means of gas turbine heat load configuration spare, the device of implementing this method and heat load vane structure |
| US5275534A (en) * | 1991-10-30 | 1994-01-04 | General Electric Company | Turbine disk forward seal assembly |
| CN103967531A (en) * | 2013-02-01 | 2014-08-06 | 西门子公司 | Film-cooled turbine blade for fluid machinery |
| CN104314621A (en) * | 2014-10-08 | 2015-01-28 | 南京航空航天大学 | Fast responding control device of turbine leaf apex gap control system based on shape memory alloy |
| CN112324518A (en) * | 2020-11-03 | 2021-02-05 | 中国民航大学 | Turbine blade with internal cooling channel based on vortex effect |
-
2021
- 2021-03-25 CN CN202110320601.0A patent/CN112780357A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN87101766A (en) * | 1986-02-04 | 1987-10-07 | 沃特·希伯特森 | The cooling means of gas turbine heat load configuration spare, the device of implementing this method and heat load vane structure |
| US5275534A (en) * | 1991-10-30 | 1994-01-04 | General Electric Company | Turbine disk forward seal assembly |
| CN103967531A (en) * | 2013-02-01 | 2014-08-06 | 西门子公司 | Film-cooled turbine blade for fluid machinery |
| CN104314621A (en) * | 2014-10-08 | 2015-01-28 | 南京航空航天大学 | Fast responding control device of turbine leaf apex gap control system based on shape memory alloy |
| CN112324518A (en) * | 2020-11-03 | 2021-02-05 | 中国民航大学 | Turbine blade with internal cooling channel based on vortex effect |
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Application publication date: 20210511 |