Engine turbine cooling air supply system with flow regulation function

Abstract

The utility model provides an engine turbine cooling air supply system with a flow regulation function. The engine turbine cooling air supply system comprises an air compressor air collection cavity and a turbine side air collection cavity. The cooling pipeline is arranged between the gas compressor gas collecting cavity and the turbine side gas collecting cavity; the adjusting device is arranged in the cooling pipeline; the adjusting device comprises a rotating shaft, fins and an elastic piece, the rotating shaft is arranged in the cooling pipeline, the fins are rotationally connected to the rotating shaft, and the elastic piece is arranged between the rotating shaft and the fins and provides restoring force for the fins. The passive adjustment air supply scheme of turbine cooling air supply can be achieved, the blade cold air consumption in the economic cruise state of the long-time working point of the engine can be remarkably reduced, the oil consumption rate of the engine is reduced, and the engine efficiency is improved.

Description

Technical Field

[0001] The utility model relates to the technical field of aviation engines, in particular to an engine turbine cooling air supply system with flow regulation. Background Art

[0002] In order to improve the thermal efficiency of civil aviation turbofan engines and reduce fuel consumption, the temperature of the turbine inlet is constantly increasing. The resulting problem is that the cooling air required for high-temperature components also increases. But at the same time, the increase in the amount of cooling air required will lead to a decrease in compressor efficiency and an increase in fuel consumption. Therefore, various means should be tried to avoid or weaken the phenomenon of increased fuel consumption caused by compressor bleed air while ensuring the amount of cooling air required for high-temperature components.

[0003] The turbine cooling flow path draws air from the high-pressure compressor intermediate stage blade tip air slit to cool the turbine. In the high-temperature takeoff state, the amount of cooling air used for the turbine needs to meet the temperature limit of the turbine blades. In the economic cruise and other states where the turbine blades have a small heat load, it is not necessary to supply cooling air equivalent to the high-temperature takeoff state, but the current lack of adjustment means on the engine is not conducive to reducing fuel consumption.

[0004] In view of this, the inventor of the present application designed an engine turbine cooling air supply system with flow regulation. Utility Model Content

[0005] The technical problem to be solved by the utility model is to overcome the defect in the prior art that the amount of cooling air intake is relatively high under the conditions of low heat load of economic cruise blades and long-term engine working point of aviation engines, and to provide an engine turbine cooling air supply system with flow regulation.

[0006] The utility model solves the above technical problems through the following technical solutions:

[0007] The utility model provides an engine turbine cooling air supply system with flow regulation, which is characterized in that the cooling air supply system comprises: a compressor air collecting chamber and a turbine side air collecting chamber; a cooling pipeline, wherein the cooling pipeline is arranged between the compressor air collecting chamber and the turbine side air collecting chamber; an adjusting device, wherein the adjusting device is arranged in the cooling pipeline; the adjusting device comprises a rotating shaft, a fin, and an elastic member, wherein the rotating shaft is arranged in the cooling pipeline, the fin is rotatably connected to the rotating shaft, and the elastic member is arranged between the rotating shaft and the fin to provide a restoring force to the fin.

[0008] According to one or more embodiments of the present invention, the rotating shaft is arranged in the cooling pipeline along the radial direction of the cooling pipeline.

[0009] According to one or more embodiments of the present invention, the fin includes a first fin and a second fin, and an angle is formed between the first fin and the second fin.

[0010] According to one or more embodiments of the present invention, the first fin and the second fin are semicircular.

[0011] According to one or more embodiments of the present invention, the angle between the first fin and the second fin is 30° to 90°.

[0012] According to one or more embodiments of the present invention, the adjusting device includes a plurality of rotating shafts, each of which is connected to at least two fins.

[0013] According to one or more embodiments of the present invention, the plurality of rotating shafts are parallel to each other on a radial plane of the cooling pipeline.

[0014] According to one or more embodiments of the present invention, the elastic member is a spring.

[0015] According to one or more embodiments of the present invention, the elastic member is an elastic sheet.

[0016] The positive and progressive effects of the utility model are:

[0017] The engine turbine cooling air supply system and cooling air supply pipeline with flow regulation have at least the following advantages:

[0018] 1. A passive regulation air supply solution capable of realizing turbine cooling air supply.

[0019] 2. It can significantly reduce the amount of cooling air used by the blades in the economic cruising state of the engine at a long-term working point, reduce the engine fuel consumption rate, and improve the engine efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] The above and other features, properties and advantages of the present invention will become more apparent through the following description in conjunction with the accompanying drawings and embodiments, in which the same reference numerals always represent the same features, wherein:

[0021] Figure 1 The utility model is a schematic diagram of an engine turbine cooling air supply system with flow regulation.

[0022] Figure 2 The utility model is a schematic diagram of the opening degree of the regulating device of the engine turbine cooling air supply system with flow regulation when the pressure difference is small.

[0023] Figure 3 The utility model is a schematic diagram of the opening degree of the regulating device of the engine turbine cooling air supply system with flow regulation when the pressure difference is relatively large.

[0024] [Reference Signs]

[0025] Compressor air chamber 100

[0026] Turbine side air collecting chamber 200

[0027] Cooling line 300

[0028] Adjustment device 400

[0029] Shaft 410

[0030] Fin 420

[0031] First fin 421

[0032] Second fin 422 DETAILED DESCRIPTION

[0033] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, the specific implementation methods of the present invention are described in detail below with reference to the accompanying drawings.

[0034] Embodiments of the utility model will now be described in detail with reference to the accompanying drawings. Reference will now be made in detail to preferred embodiments of the utility model, examples of which are shown in the accompanying drawings. Wherever possible, the same reference numerals will be used in all drawings to represent the same or similar parts. In addition, although the terms used in the utility model are selected from well-known and commonly used terms, some of the terms mentioned in the utility model specification may be selected by the applicant at his or her discretion, and their detailed meanings are explained in the relevant parts of the description herein. In addition, it is required to understand the utility model not only by the actual terms used, but also by the meaning implied by each term.

[0035] In the high-temperature takeoff state, the cooling air volume for the turbine needs to meet the cooling design requirements. In the cruise state where the turbine blades have a small heat load, it is not necessary to supply the same amount of cooling air as in the high-temperature takeoff state. However, the current lack of adjustment means on the engine is not conducive to reducing fuel consumption.

[0036] like Figure 1 to Figure 3 As shown, the utility model provides an engine turbine cooling air supply system with flow regulation, characterized in that the cooling air supply system comprises:

[0037] The compressor collecting chamber 100 and the turbine side collecting chamber 200;

[0038] A cooling pipeline 300, the cooling pipeline 300 is arranged between the compressor air collecting cavity 100 and the turbine side air collecting cavity 200;

[0039] The adjusting device 400 is arranged in the cooling pipeline 300; the adjusting device 400 includes a rotating shaft 410, a fin 420, and an elastic member. The rotating shaft 410 is arranged in the cooling pipeline 300, and the fin 420 is rotatably connected to the rotating shaft 410. The elastic member is arranged between the rotating shaft 410 and the fin 420 to provide a restoring force to the fin 420.

[0040] Figure 1 The figure shows the turbine cooling system, where the arrow indicates the direction of the cooling flow path, which is generally drawn from the middle stage of the compressor, led out through the compressor collecting cavity 100, and after passing through the cooling pipeline 300, reaches the turbine side collecting cavity 200, and provides the gas to the turbine guide vanes or other parts that need cooling. The pressure of the compressor collecting cavity 100 is P1, and the pressure of the turbine side collecting cavity 200 is P2, P1>P2.

[0041] The fin 420 can rotate on the rotating shaft 410, and the rotation angle of the fin 420 determines the opening of the regulating device 400. The larger the opening, the more gas flows; the smaller the opening, the less gas flows. The elastic member provides a restoring force to the fin 420. When the engine turbine cooling air supply system is not working, the fin 420 is closed, and the edge of the fin 420 is against the inner wall of the cooling pipeline 300; when the engine turbine cooling air supply system is working, the pressure difference between the pressure P1 of the compressor collecting chamber 100 and the pressure P2 of the turbine side collecting chamber 200 causes the fin 420 to open, and the greater the pressure difference, the greater the opening, and the more gas flows.

[0042] The engine turbine cooling air supply system with flow regulation provided by the utility model is a pressure difference driven air supply system. Under conditions of low blade heat load such as cruising state, the cold air for cooling the turbine is passively controlled to reduce the amount of cold air used. By setting a pressure difference driven regulating device 400 on the cooling pipeline 300, the cold air flow is controlled: when the blade heat load is large, the regulating device 400 has a large flow capacity, thereby providing a large amount of cold air. When the blade heat load is small, the flow capacity is small, reducing the amount of cold air, thereby reducing the engine fuel consumption rate and improving the engine efficiency.

[0043] like Figure 2 and Figure 3 As shown, as a preferred embodiment of the engine turbine cooling air supply system with flow regulation of the utility model, the rotating shaft 410 is arranged in the cooling pipeline 300 along the radial direction of the cooling pipeline 300.

[0044] like Figure 2 and Figure 3 As shown, as a preferred embodiment of the engine turbine cooling air supply system with flow regulation of the utility model, the fin 420 includes a first fin 421 and a second fin 422, and an angle is formed between the first fin 421 and the second fin 422.

[0045] As a preferred embodiment of the engine turbine cooling air supply system with flow regulation of the utility model, the first fin 421 and the second fin 422 are semicircular.

[0046] The semicircular first fin 421 and the second fin 422 can match the inner wall of the cooling pipe 300 with a circular cross-section.

[0047] As a preferred embodiment of the engine turbine cooling air supply system with flow regulation of the utility model, the angle between the first fin 421 and the second fin 422 is 30° to 90°.

[0048] As a preferred embodiment of the engine turbine cooling air supply system with flow regulation of the utility model, the regulating device 400 includes a plurality of rotating shafts 410 , and each rotating shaft 410 is connected to at least two fins 420 .

[0049] As a preferred embodiment of the engine turbine cooling air supply system with flow regulation of the utility model, a plurality of rotating shafts 410 are parallel to each other on the radial plane of the cooling pipeline 300 .

[0050] As a preferred implementation of the engine turbine cooling air supply system with flow regulation of the utility model, the elastic member is a spring.

[0051] As a preferred implementation of the engine turbine cooling air supply system with flow regulation of the utility model, the elastic member is an elastic sheet.

[0052] The regulating device 400 arranged in the cooling pipeline 300 is mainly composed of fins 420 and a rotating shaft 410 , and a spring or other elastic sheet is arranged between the fins 420 and the rotating shaft 410 .

[0053] like Figure 2 As shown, this is the opening degree of the regulating mechanism when the aircraft is cruising or in other states. When the pressure difference is small, such as when the aircraft is cruising, the bleed air pressure on the compressor side is low, and the bleed air pressure difference between the compressor and the exhaust air is small. The fin 420 of the regulating device 400 opens at a large angle, the flow area of ​​the cooling pipeline 300 is small, and the air flow rate through the cooling pipeline 300 is small, so that the regulating device 400 controls the bleed air flow rate.

[0054] like Figure 3 As shown, this is the opening degree of the regulating mechanism when the aircraft is taking off, etc. Under conditions of large pressure difference such as when the aircraft is taking off, the cooling flow demand is large. At the same time, the bleed air pressure in this state is large, and the pressure difference on both sides of the regulating device 400 is also large. The opening angle of the fin 420 is small, the flow area is large, and the air flow through the cooling pipeline 300 is also large, thereby being able to meet the cooling demand.

[0055] The elastic force of the spring or elastic sheet on the rotating shaft 410 is determined according to the different pressure differences between the state of large pressure difference and the state of small pressure difference and the flow area requirements of the respective cooling pipelines 300.

[0056] The utility model discloses an engine turbine cooling air supply system with flow regulation, which can solve the problem of high cooling air volume under the low heat load conditions of economic cruise blades and long-term engine working point of aviation engines, further reduce engine fuel consumption rate and improve engine efficiency.

[0057] In summary, the engine turbine cooling air supply system with flow regulation of the utility model has the following advantages:

[0058] 1. A passive regulation air supply solution capable of realizing turbine cooling air supply.

[0059] 2. It can significantly reduce the amount of cooling air used by the blades in the economic cruising state of the engine at a long-term working point, reduce the engine fuel consumption rate, and improve the engine efficiency.

[0060] Although the specific embodiments of the present invention are described above, those skilled in the art should understand that these are only examples, and the protection scope of the present invention is defined by the appended claims. Those skilled in the art may make various changes or modifications to these embodiments without departing from the principle and essence of the present invention, but these changes and modifications fall within the protection scope of the present invention.

Claims

1. An engine turbine cooling air supply system with flow regulation, characterized in that: The cooling air supply system comprises: Compressor air collecting chamber and turbine side air collecting chamber; A cooling pipeline, wherein the cooling pipeline is arranged between the compressor air collecting chamber and the turbine side air collecting chamber; The adjusting device is arranged in the cooling pipeline; the adjusting device comprises a rotating shaft, a fin, and an elastic member, the rotating shaft is arranged in the cooling pipeline, the fin is rotatably connected to the rotating shaft, and the elastic member is arranged between the rotating shaft and the fin to provide a restoring force to the fin.

2. The engine turbine cooling air supply system with flow regulation according to claim 1, characterized in that: The rotating shaft is arranged in the cooling pipeline along the radial direction of the cooling pipeline.

3. The engine turbine cooling air supply system with flow regulation according to claim 2, characterized in that: The fins include a first fin and a second fin, and an angle is formed between the first fin and the second fin.

4. The engine turbine cooling air supply system with flow regulation according to claim 3, characterized in that: The first fin and the second fin are semicircular.

5. The engine turbine cooling air supply system with flow regulation according to claim 3, characterized in that: The included angle between the first fin and the second fin is 30° to 90°.

6. The engine turbine cooling air supply system with flow regulation according to claim 2, characterized in that: The adjusting device comprises a plurality of rotating shafts, each of which is connected with at least two fins.

7. The engine turbine cooling air supply system with flow regulation according to claim 6, characterized in that: The plurality of rotating shafts are parallel to each other on a radial plane of the cooling pipeline.

8. The engine turbine cooling air supply system with flow regulation according to claim 1, characterized in that: The elastic member is a spring.

9. The engine turbine cooling air supply system with flow regulation according to claim 1, characterized in that: The elastic member is an elastic sheet.

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