CN112855283B - Engine prerotation system capable of improving receiving hole flow coefficient - Google Patents
Engine prerotation system capable of improving receiving hole flow coefficient Download PDFInfo
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- CN112855283B CN112855283B CN202110028802.3A CN202110028802A CN112855283B CN 112855283 B CN112855283 B CN 112855283B CN 202110028802 A CN202110028802 A CN 202110028802A CN 112855283 B CN112855283 B CN 112855283B
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- cover plate
- prerotation
- disc
- turbine
- nozzle
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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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
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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
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/08—Heating, heat-insulating or cooling means
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention provides an engine prerotation system capable of improving the flow coefficient of a receiving hole, which comprises a prerotation nozzle disc, a turbine cover plate disc and a turbine disc, wherein a plurality of prerotation nozzles are uniformly distributed on the prerotation nozzle disc along the circumferential direction, a plurality of receiving holes are uniformly distributed on the turbine cover plate disc along the circumferential direction, a prerotation cavity is formed between the prerotation nozzle disc and the turbine cover plate disc, a cover plate cavity is formed between the turbine cover plate disc and the turbine disc, aiming at the characteristic that the outlet airflow of the prerotation nozzle has circumferential speed, an attack angle alpha of the outlet airflow of the prerotation nozzle flowing to the cover plate disc is calculated according to the absolute speed C of the airflow at the outlet of the prerotation nozzle, the rotating speed U of a turbine rotor and an included angle beta between the axis of the prerotation nozzle and the circumferential direction, and the preset included angle between the axis of the receiving holes and the normal line of the turbine cover plate disc is used for enabling the outlet airflow of the prerotation nozzle to flow into the receiving hole at a zero angle, thereby reducing the flow resistance of the air flow through the receiving aperture in the turbine cover plate to increase the flow coefficient of the receiving aperture.
Description
Technical Field
The invention relates to the field of ground gas turbines and aero-engines, in particular to an engine pre-rotation system, and particularly relates to improvement of a turbine cover plate disc structure in the engine pre-rotation system, so that the flow coefficient of a receiving hole in the pre-rotation system is increased, the flow of cooling gas is improved, the cooling effect is improved, and the heat load of a wheel disc is reduced.
Background
The turbine part of the aircraft engine is generally provided with a prerotation system structure, the prerotation system is an important component of an air system of the engine, and the prerotation system has the functions of reducing the temperature of cooling air for cooling turbine rotor blades, improving the cooling effect of the blades and reducing the consumption of cooling air flow. The basic principle of the prerotation system is to generate a circumferential speed of the cooling gas before entering the blades along the rotation direction, namely, the prerotation is generated, so that the relative total temperature of the cooling gas relative to the rotating disk can be reduced, and a better cooling effect is provided for the turbine part.
In terms of its structure, the engine prerotation system, as shown in fig. 1, is mainly composed of the following parts: the turbine cover plate structure comprises a pre-rotation nozzle 2, a pre-rotation cavity 3, a cover plate cavity 6 and a receiving hole 5, wherein the pre-rotation nozzle 2 is arranged on a pre-rotation nozzle disc 1, the receiving hole 5 is arranged on a turbine cover plate disc 4, the pre-rotation cavity 3 is formed between the pre-rotation nozzle disc 1 and the turbine cover plate disc 4, and the cover plate cavity 6 is formed between the turbine cover plate disc 4 and a turbine disc 7. Cooling gas passes through the pre-rotation nozzle 2 on the pre-rotation nozzle disc 1, is expanded and accelerated to obtain a circumferential speed, and enters the pre-rotation cavity 3; the gas then enters the shroud cavity 6 through the receiving holes 5 in the turbine shroud disk 4 and flows radially outwardly in the shroud cavity 6 to provide cooling gas to the blades through the gas supply holes at the root of the blade dovetail. It can be seen that the main structure of the pre-swirl system is composed of holes (pre-swirl nozzle 2, receiving hole 5) and disk cavities (pre-swirl cavity 3, cover plate cavity 6), and the magnitude of the flow resistance of these elements has a significant influence on the performance of the pre-swirl system. The smaller the flow resistance of each element, the higher the cooling gas flow rate that can be provided under the same conditions, and the better the cooling effect. It is therefore desirable to reduce the flow resistance of the pre-swirl system components.
Disclosure of Invention
Aiming at the technical requirements, the invention provides the engine prerotation system capable of improving the flow coefficient of a receiving hole in order to reduce the flow resistance of elements in the engine prerotation system, further improve the flow of cooling gas under the same condition and improve the cooling effect. Aiming at the characteristic that the airflow at the outlet of the prewhirl nozzle has the circumferential speed, the included angle between the axis of the receiving hole and the normal line of the cover plate disc is changed, so that the airflow at the outlet of the prewhirl nozzle flows into the receiving hole at a zero attack angle, the flow resistance of the airflow at the receiving hole on the cover plate disc of the turbine is reduced, the flow coefficient of the receiving hole is increased, the flow of cooling gas is increased, the cooling effect is improved, the heat load of the wheel disc is reduced, and the working performance of a prewhirl system of an engine is improved.
In order to achieve the technical goals, the technical scheme adopted by the invention is as follows:
an engine prerotation system capable of improving the flow coefficient of receiving holes comprises a prerotation nozzle disc, a turbine cover plate disc and a turbine disc, wherein a plurality of prerotation nozzles are uniformly distributed on the prerotation nozzle disc along the circumferential direction, a plurality of receiving holes are uniformly distributed on the turbine cover plate disc along the circumferential direction, a prerotation cavity is formed between the prerotation nozzle disc and the turbine cover plate disc, and a cover plate cavity is formed between the turbine cover plate disc and the turbine disc,
calculating an attack angle alpha of the airflow at the outlet of the prerotation nozzle flowing to the cover plate disc according to the absolute speed C of the airflow at the outlet of the prerotation nozzle, the rotating speed U of the turbine rotor and an included angle beta between the axis of the prerotation nozzle and the circumferential direction,
and setting an included angle between the axis of the receiving hole and the normal of the turbine cover plate disc according to the attack angle alpha of the pre-rotation nozzle outlet airflow flowing to the cover plate disc, so that the pre-rotation nozzle outlet airflow flows into the receiving hole at a zero attack angle.
Preferably, the attack angle α of the pre-swirl nozzle outlet air flow to the cover plate disc is calculated as:
preferably, an angle between an axis of the receiving hole and a normal line of the turbine cover plate is set to be equal to an attack angle α of the pre-swirl nozzle outlet airflow to the cover plate, so that the pre-swirl nozzle outlet airflow flows into the receiving hole at a zero attack angle to improve a flow coefficient of the receiving hole on the turbine cover plate.
Furthermore, in order to improve the strength of the receiving hole on the turbine cover plate disc, the punching part on the turbine cover plate disc is provided with a local thickening structure.
The invention discloses an engine prerotation system capable of improving the receiving hole flow coefficient, which has the working principle that: aiming at the characteristic that the airflow at the outlet of the pre-rotation nozzle has circumferential speed, the included angle between the axis of the receiving hole on the turbine cover plate disc and the normal line of the turbine cover plate disc is set to be equal to the attack angle alpha of the airflow at the outlet of the pre-rotation nozzle flowing to the cover plate disc, so that the airflow at the outlet of the pre-rotation nozzle flows into each receiving hole on the turbine cover plate disc at a zero attack angle, the flow resistance of the airflow passing through the receiving hole on the turbine cover plate disc is reduced, the flow coefficient of the receiving hole is improved, and the flow rate of cooling air is increased.
Compared with the prior art, the engine prewhirl system capable of improving the receiving hole flow coefficient has the remarkable technical effects that: aiming at the characteristic that the airflow at the outlet of the prewhirl nozzle has circumferential speed, the invention enables the airflow at the outlet of the prewhirl nozzle to flow into the receiving hole at a zero attack angle by changing the included angle between the axis of the receiving hole and the normal of the cover plate disc, thereby reducing the flow resistance of the airflow passing through the receiving hole on the turbine cover plate disc, increasing the flow coefficient of the receiving hole, increasing the flow of cooling gas, improving the cooling effect, reducing the heat load of a wheel disc and improving the working performance of a prewhirl system of an engine.
Drawings
Fig. 1 is a schematic structural diagram of a pre-rotation system of a conventional engine.
Fig. 2 is a triangular schematic view of the air flow at the outlet of the pre-swirl nozzle.
FIG. 3 is a schematic view of a receiving hole in a turbine cover plate.
FIG. 4 is a schematic view of a locally thickened structure at a receiving hole in a turbine cover plate.
In the figures, the meaning of the reference numerals is as follows:
the device comprises a prerotation nozzle disc 1, a prerotation nozzle 2, a prerotation cavity 3, a turbine cover plate disc 4, a receiving hole 5, a cover plate cavity 6 and a turbine disc 7.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below with reference to the accompanying drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, but not all embodiments of the invention. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention. The structure and technical scheme of the present invention are further described in detail with reference to the accompanying drawings, and an embodiment of the present invention is provided.
The invention discloses an engine prerotation system capable of improving the flow coefficient of receiving holes, which comprises a prerotation nozzle disc 1, a turbine cover plate disc 4 and a turbine disc 7, wherein a plurality of prerotation nozzles 2 are uniformly distributed on the prerotation nozzle disc 1 along the circumferential direction, a plurality of receiving holes 5 are uniformly distributed on the turbine cover plate disc 4 along the circumferential direction, a prerotation cavity 3 is formed between the prerotation nozzle disc 1 and the turbine cover plate disc 4, and a cover plate cavity 6 is formed between the turbine cover plate disc 4 and the turbine disc 7, as shown in figure 1.
As shown in FIGS. 2 and 3, aiming at the characteristic that the outlet airflow of the pre-rotation nozzle has circumferential velocity, in order to reduce the flow resistance of the airflow passing through the receiving hole 5 on the turbine cover plate 4, increase the flow coefficient of the receiving hole and increase the flow rate of the cooling air, the invention changes the included angle between the axis of the receiving hole and the normal line of the cover plate, so that the outlet airflow of the pre-rotation nozzle flows into the receiving hole at a zero attack angle. Specifically, according to the velocity triangle of the air flow at the outlet of the pre-rotation nozzle, as shown in fig. 2, C is the absolute outlet velocity of the pre-rotation nozzle, U is the rotation speed of the rotor, W is the relative velocity of the air flow at the outlet of the pre-rotation nozzle relative to the rotor, and β is the included angle between the axis of the pre-rotation nozzle and the circumferential direction. It can be seen that the pre-swirl nozzle outlet flow is at an angle of attack α towards the cover plate disc. The angle α can be calculated from the ideal outflow speed and rotational speed:
to increase the flow coefficient of the receiving holes in the turbine cover plate, the receiving holes are designed such that the air flow enters the receiving holes at a zero angle of attack, as shown in fig. 3, and the axes of the receiving holes are offset from the normal of the cover plate by an angle α. Specifically, the angle between the axis of the receiving hole and the normal of the turbine shroud plate is set according to the angle of attack α of the pre-swirl nozzle outlet airflow to the shroud plate so that the pre-swirl nozzle outlet airflow flows into the receiving hole at zero angle of attack. For this purpose, an included angle between the axis of the receiving hole and the normal line of the turbine cover plate is set to be equal to an attack angle alpha of the pre-swirl nozzle outlet airflow flowing to the cover plate, so that the pre-swirl nozzle outlet airflow flows into the receiving hole at a zero attack angle, and the flow coefficient of the receiving hole on the turbine cover plate is improved.
After the angle between the axis of the receiving hole and the normal of the turbine shroud is set to be equal to the angle of attack α of the outlet airflow of the pre-swirl nozzle to the shroud, the structure is adopted in which the punching part is locally thickened in order to meet the requirement of the strength of the inclined hole, as shown in fig. 4.
The invention discloses an engine prerotation system capable of improving the receiving hole flow coefficient, which has the working principle that: aiming at the characteristic that the airflow at the outlet of the pre-spinning nozzle has circumferential speed, the invention sets the included angle between the axis of the receiving hole on the turbine cover plate disc and the normal line of the turbine cover plate disc to be equal to the attack angle alpha of the airflow at the outlet of the pre-spinning nozzle flowing to the cover plate disc, so that the airflow at the outlet of the pre-spinning nozzle flows into each receiving hole on the turbine cover plate disc at a zero attack angle, thereby reducing the flow resistance of the airflow passing through the receiving hole on the turbine cover plate disc, improving the flow coefficient of the receiving hole and increasing the flow rate of cooling gas.
The object of the present invention is fully effectively achieved by the above embodiments. Those skilled in the art will appreciate that the present invention includes, but is not limited to, what is described in the accompanying drawings and the foregoing detailed description. While the invention has been described in connection with what is presently considered to be the most practical and preferred embodiment, it is to be understood that the invention is not to be limited to the disclosed embodiment, but on the contrary, is intended to cover various modifications within the spirit and scope of the appended claims.
Claims (3)
1. An engine prerotation system capable of improving the flow coefficient of receiving holes comprises a prerotation nozzle disc, a turbine cover plate disc and a turbine disc, wherein a plurality of prerotation nozzles are uniformly distributed on the prerotation nozzle disc along the circumferential direction, a plurality of receiving holes are uniformly distributed on the turbine cover plate disc along the circumferential direction, a prerotation cavity is formed between the prerotation nozzle disc and the turbine cover plate disc, and a cover plate cavity is formed between the turbine cover plate disc and the turbine disc,
calculating an attack angle alpha of the airflow at the outlet of the prerotation nozzle flowing to the cover plate disc according to the absolute speed C of the airflow at the outlet of the prerotation nozzle, the rotating speed U of the turbine rotor and an included angle beta between the axis of the prerotation nozzle and the circumferential direction,
setting an included angle between the axis of the receiving hole and the normal of the turbine cover plate disc according to an attack angle alpha of the pre-rotation nozzle outlet airflow flowing to the cover plate disc, so that the pre-rotation nozzle outlet airflow flows into the receiving hole at a zero attack angle;
the attack angle alpha of the airflow at the outlet of the pre-rotation nozzle flowing to the cover plate disc is calculated according to the formula:
2. the engine prerotation system capable of improving the receiving hole flow coefficient according to claim 1, wherein an angle between an axis of the receiving hole and a normal line of a turbine cover plate is set to be equal to an attack angle α of the prerotation nozzle outlet airflow to the cover plate, so that the prerotation nozzle outlet airflow flows into the receiving hole at a zero attack angle to improve the flow coefficient of the receiving hole on the turbine cover plate.
3. The system of claim 1, wherein the perforated portion of the turbine cover plate has a locally thickened structure to increase the strength of the receiving hole of the turbine cover plate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110028802.3A CN112855283B (en) | 2021-01-11 | 2021-01-11 | Engine prerotation system capable of improving receiving hole flow coefficient |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110028802.3A CN112855283B (en) | 2021-01-11 | 2021-01-11 | Engine prerotation system capable of improving receiving hole flow coefficient |
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| Publication Number | Publication Date |
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| CN112855283A CN112855283A (en) | 2021-05-28 |
| CN112855283B true CN112855283B (en) | 2022-05-20 |
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| CN202110028802.3A Active CN112855283B (en) | 2021-01-11 | 2021-01-11 | Engine prerotation system capable of improving receiving hole flow coefficient |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN116220913B (en) * | 2023-05-08 | 2023-08-18 | 中国航发四川燃气涡轮研究院 | Low-loss engine pre-rotation air supply system |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108194147A (en) * | 2018-01-12 | 2018-06-22 | 南京航空航天大学 | One kind is for the azimuthal nozzle arrangements of system band of radially prewhirling |
| CN109458229A (en) * | 2018-12-20 | 2019-03-12 | 中国航发四川燃气涡轮研究院 | A kind of turbine disk chamber seal structure of band bypass bleed |
| CN109630209A (en) * | 2018-12-10 | 2019-04-16 | 中国航发四川燃气涡轮研究院 | A kind of band is prewhirled the turbine disk chamber seal structure of bleed |
| CN110145374A (en) * | 2018-02-14 | 2019-08-20 | 中国航发商用航空发动机有限责任公司 | Engine is prewhirled system |
| CN110905606A (en) * | 2019-12-05 | 2020-03-24 | 中国航发四川燃气涡轮研究院 | Turbine disc cavity sealing structure with bypass air entraining function |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2840351B1 (en) * | 2002-05-30 | 2005-12-16 | Snecma Moteurs | COOLING THE FLASK BEFORE A HIGH PRESSURE TURBINE BY A DOUBLE INJECTOR SYSTEM BOTTOM BOTTOM |
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- 2021-01-11 CN CN202110028802.3A patent/CN112855283B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108194147A (en) * | 2018-01-12 | 2018-06-22 | 南京航空航天大学 | One kind is for the azimuthal nozzle arrangements of system band of radially prewhirling |
| CN110145374A (en) * | 2018-02-14 | 2019-08-20 | 中国航发商用航空发动机有限责任公司 | Engine is prewhirled system |
| CN109630209A (en) * | 2018-12-10 | 2019-04-16 | 中国航发四川燃气涡轮研究院 | A kind of band is prewhirled the turbine disk chamber seal structure of bleed |
| CN109458229A (en) * | 2018-12-20 | 2019-03-12 | 中国航发四川燃气涡轮研究院 | A kind of turbine disk chamber seal structure of band bypass bleed |
| CN110905606A (en) * | 2019-12-05 | 2020-03-24 | 中国航发四川燃气涡轮研究院 | Turbine disc cavity sealing structure with bypass air entraining function |
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| CN112855283A (en) | 2021-05-28 |
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