CN113719623B - Valve for annular channel of aero-engine - Google Patents
Valve for annular channel of aero-engine Download PDFInfo
- Publication number
- CN113719623B CN113719623B CN202111079753.2A CN202111079753A CN113719623B CN 113719623 B CN113719623 B CN 113719623B CN 202111079753 A CN202111079753 A CN 202111079753A CN 113719623 B CN113719623 B CN 113719623B
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- Prior art keywords
- valve
- annular channel
- annular
- along
- sealing
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16K—VALVES; TAPS; COCKS; ACTUATING-FLOATS; DEVICES FOR VENTING OR AERATING
- F16K3/00—Gate valves or sliding valves, i.e. cut-off apparatus with closing members having a sliding movement along the seat for opening and closing
- F16K3/02—Gate valves or sliding valves, i.e. cut-off apparatus with closing members having a sliding movement along the seat for opening and closing with flat sealing faces; Packings therefor
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16K—VALVES; TAPS; COCKS; ACTUATING-FLOATS; DEVICES FOR VENTING OR AERATING
- F16K27/00—Construction of housing; Use of materials therefor
- F16K27/04—Construction of housing; Use of materials therefor of sliding valves
- F16K27/044—Construction of housing; Use of materials therefor of sliding valves slide valves with flat obturating members
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16K—VALVES; TAPS; COCKS; ACTUATING-FLOATS; DEVICES FOR VENTING OR AERATING
- F16K3/00—Gate valves or sliding valves, i.e. cut-off apparatus with closing members having a sliding movement along the seat for opening and closing
- F16K3/30—Details
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16K—VALVES; TAPS; COCKS; ACTUATING-FLOATS; DEVICES FOR VENTING OR AERATING
- F16K31/00—Actuating devices; Operating means; Releasing devices
- F16K31/44—Mechanical actuating means
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Lift Valve (AREA)
Abstract
The present disclosure provides a valve for an aircraft engine annular channel, comprising: a plurality of unit bodies which are all arranged in the annular channel; the plurality of unit bodies are uniformly distributed in the annular channel along the circumferential direction; each unit body comprises a plurality of valve plates which are distributed along the flow direction; the valve plate is in sliding fit with the annular channel and is arranged in a sliding way along the circumferential direction; the valve plates of each unit body can be unfolded along the circumferential direction to form a sector ring-shaped sealing structure; when each unit body is in an unfolding state, the plurality of fan-shaped annular sealing structures are paved with the whole annular channel along the circumferential direction; a sealing end face is arranged between any two adjacent unit bodies; the sealing end face is positioned on the last valve plate along the flow direction; one side of the sealing end face is connected with the valve plates, and the other side of the sealing end face opposite to the sealing end face extends to at least the first valve plate along the flow direction along the direction opposite to the flow direction; the sealing end face is used for sealing a gap between two adjacent unit bodies.
Description
Technical Field
The disclosure relates to the technical field of aeroengines, and in particular relates to a valve for an annular passage of an aeroengine.
Background
With the technical development of the traditional aero-engine, a variable cycle engine concept appears, and the variable cycle engine becomes the main stream direction. The first variable cycle engine validator XA100 engine from GE in the united states has been tested 3 months in 2021. The intended goals of a 10% increase in thrust and a 25% increase in fuel efficiency are achieved. The most typical characteristic is that the bypass ratio of the engine is changed in a larger range through the opening and closing of the third bypass, so that the flow regulating capability of the engine is further enhanced, and the engine is promoted to change the working state in a wider range so as to meet different task demands.
Normally, the bypass is opened and closed by a "mode selector valve". Because the duct section is annular, the "mode selector valve" generally adopts a "fenestration" structure. I.e. the valve consists of a frame and a valve plate. The structure has the advantages of simple structure, large flow resistance caused by large flow area occupied by the frame structure, and reduced thrust of the engine.
Disclosure of Invention
To address at least one of the above-mentioned technical problems, the present disclosure provides a valve for an aircraft engine annular passage.
According to one aspect of the present disclosure, a valve for an aircraft engine annular passage comprises: a plurality of unit bodies uniformly distributed in the annular channel along the circumferential direction;
each unit body is of a folding fan type structure and comprises a plurality of valve plates distributed along the flow direction, at least one end of each valve plate is hinged with a connecting rod, and two adjacent valve plates are movably connected through at least two connecting rods;
the valve plate is in sliding fit with the annular channel, and the valve plate is arranged in a sliding manner along the circumferential direction;
the valve plates of each unit body can be unfolded along the circumferential direction to form a fan-shaped annular sealing structure;
when each unit body is in an unfolding state, the plurality of fan-shaped annular sealing structures circumferentially seal the whole annular channel.
According to at least one embodiment of the present disclosure, a sealing end face is provided between any adjacent two unit bodies; the sealing end face is used for sealing a gap between two adjacent unit bodies in the unfolded state.
According to at least one embodiment of the present disclosure, 3 to 5 valve plates are provided for each unit body; and/or
3-9 unit bodies are arranged in each annular channel section.
According to at least one embodiment of the present disclosure, each of the unit bodies has a streamline shape along a flow direction when in a converging state.
According to at least one embodiment of the present disclosure, the projected shape and projected area of each valve sheet on the same cross section of the annular channel are the same.
According to at least one embodiment of the present disclosure, each of the valve plates has a fan shape centered on the center of the annular channel.
According to at least one embodiment of the present disclosure, further comprising an actuation ring located outside the annular channel;
the side wall of the annular channel opposite to the actuating ring is a supporting side wall;
the two ends of the valve plate in the radial direction are respectively a connecting end and a sliding end;
the connecting end is hinged to the actuating ring;
the sliding end and the supporting side wall are provided with a sliding connection structure;
the actuating ring is used for driving the valve plate to be unfolded along the circumferential direction.
According to at least one embodiment of the present disclosure, the sliding connection structure includes an annular rib and an annular groove into which the annular rib is fitted.
According to at least one embodiment of the present disclosure, the actuating ring is provided with a plurality of actuating rings, and the actuating rings are arranged along the flow direction;
the actuating ring is positioned between two adjacent valve plates along the flow direction;
each actuating ring is provided with a strip hole arranged along the radial direction;
a connecting rod is inserted into the strip hole;
connecting rods are hinged to the connecting ends of two adjacent valve plates, one ends of the two connecting rods are hinged to the connecting ends of the two valve plates respectively, and the other ends of the two connecting rods are hinged to the two ends of the connecting rods respectively.
According to at least one embodiment of the present disclosure, the device further comprises a chain located outside the annular channel, wherein the chain is enclosed into an annular shape and is movably connected with the connecting rod, and the chain is used for driving the unit body to expand or converge.
The beneficial effects of the present disclosure are:
(1) The valve for the annular passage of the aero-engine is converged into a streamline shape along the flow direction when being closed, and the flow resistance is small;
(2) The valve for the annular channel of the aero-engine can be paved with the whole annular channel when being unfolded, and has good tightness when the duct is closed due to the effect of the sealing end face;
(3) The valve for the annular channel of the aero-engine is simple in structure, can be produced, installed and replaced in a modularized mode, and can be adjusted by only rotating the actuating ring, and the structural reliability and the adjustment reliability are both high.
(4) The valve for the annular channel of the aero-engine can be suitable for large-amplitude adjustment of two ducts, can be used for complete switching of an air flow channel of the engine, and is suitable for power forms with multi-channel characteristics such as turbine-based combined power.
Drawings
The accompanying drawings, which are included to provide a further understanding of the disclosure and are incorporated in and constitute a part of this specification, illustrate exemplary embodiments of the disclosure and together with the description serve to explain the principles of the disclosure.
FIG. 1 is a schematic illustration of a valve for an aircraft engine annular passage according to an embodiment of the present disclosure.
Fig. 2 is a schematic illustration of a valve for an aircraft engine annular channel (with intervening and outer gates omitted) according to an embodiment of the disclosure.
Fig. 3 is a schematic view of a unit body in an inner and outer annular channel of the valve for an annular channel of an aircraft engine shown in fig. 1.
Fig. 4 is a schematic illustration of the connection of the unit body to the actuating ring in the valve for the annular channel of an aircraft engine shown in fig. 1.
Fig. 5 is a schematic illustration of closing the outer annular channel and opening the inner annular channel with the valve for an aircraft engine annular channel shown in fig. 1.
Fig. 6 is a schematic illustration of the valve for an aircraft engine annular channel shown in fig. 1 closing an inner annular channel and opening an outer annular channel.
FIG. 7 is a schematic illustration of a semi-closed outer annular passage and a semi-closed inner annular passage with the valve for an aircraft engine annular passage shown in FIG. 1.
Reference numerals: 10-unit body; 11-valve plates; 12-sealing end surfaces; 13-a connecting rod; 14-an annular groove; 20-actuating the ring; 21-elongated holes; 30-connecting rods; 40-a housing; 41-an inner machine brake; 42-an external machine gate; 43-intervening gate; 44-annular channel.
Detailed Description
The present disclosure is described in further detail below with reference to the drawings and the embodiments. It is to be understood that the specific embodiments described herein are merely illustrative of the relevant content and not limiting of the present disclosure. It should be further noted that, for convenience of description, only a portion relevant to the present disclosure is shown in the drawings.
In addition, embodiments of the present disclosure and features of the embodiments may be combined with each other without conflict. The present disclosure will be described in detail below with reference to the accompanying drawings in conjunction with embodiments.
The term "flow direction" as used herein refers to the flow direction of air, i.e., the axial direction of the annular passage 44, "circumferential" refers to the circumferential direction of the annular passage 44, and "radial" refers to the radial direction of the cross section of the annular passage 44.
As shown in fig. 1, the housing 40 of the aero-engine includes a plurality of engine gates sleeved in sequence from inside to outside, the annular channel 44 is formed between any two adjacent engine gates, and the valve of the present disclosure is disposed in each annular channel 44. Taking two annular channels 44 as an example in this embodiment, specifically, the housing 40 includes an inner gate 41, an intermediate gate 43 and an outer gate 42 sleeved in sequence from inside to outside; a first annular channel 44 is formed between the inner gate 41 and the intermediate gate 43, and a second annular channel 44 is formed between the intermediate gate 43 and the outer gate 42.
As shown in fig. 1-7, according to a first embodiment of the present disclosure, there is provided a valve for an aircraft engine annular channel 44, comprising: a plurality of unit bodies 10 uniformly distributed in the circumferential direction within the annular channel 44; each unit body 10 is of a folding fan structure and comprises a plurality of valve plates 11 distributed along the flow direction, at least one end of each valve plate 11 is hinged with a connecting rod 13, and two adjacent valve plates 11 are movably connected through at least two connecting rods 13; the valve plate 11 is in sliding fit with the annular channel 44, and the valve plate 11 is arranged in a sliding manner along the circumferential direction; the plurality of valve plates 11 of each unit body 10 can be unfolded along the circumferential direction and form a fan-shaped ring-shaped sealing structure; when each unit cell 10 is in the expanded state, the plurality of sector-ring seal structures circumferentially close the entire annular channel 44.
The number of the unit bodies 10 is determined according to the cross-street area of the annular channel 44 and the size of the unit bodies 10 after being unfolded, and any number, for example 3 to 9, can be set; in the present embodiment, the number of unit cells 10 is 8.
The annular channel 44 forms an annular chute, the valve plate 11 slides circumferentially in the annular channel 44 to achieve the purpose of expanding or converging the unit body 10, compared with the prior art, the frame is omitted, the flow area occupying the annular channel 44 is smaller, thereby reducing the flow resistance and further improving the thrust of the aeroengine.
According to one embodiment of the present disclosure, a sealing end face 12 is provided between any adjacent two unit bodies 10; the seal end face 12 is used to seal a gap between adjacent two unit bodies 10.
Since the valve plates 11 of the same unit body 10 are arranged along the flow direction, when the unit body 10 is unfolded, a gap exists between the first valve plate 11 of one unit body 10 along the flow direction and the last valve plate 11 of the adjacent unit body 10 along the flow direction, and the gap is sealed by arranging the sealing end face 12, so that the sealing performance is better after the unit body 10 is unfolded.
The sealing end surface 12 may be located on the last valve plate 11 in the flow direction, specifically, one side of the sealing end surface 12 is connected to one side of the last valve plate 11, and the other side opposite to the sealing end surface 12 extends at least to the first valve plate 11 in the flow direction in the direction opposite to the flow direction.
According to one embodiment of the present disclosure, each unit 10 has a streamline shape along the flow direction when each unit 10 is in the converging state, that is, the cross section of the unit 10 after converging is gradually reduced along the flow direction, so as to reduce the air flow resistance.
According to one embodiment of the present disclosure, the projected shape and projected area of each valve sheet 11 on the same cross section of the annular channel 44 are the same.
According to one embodiment of the present disclosure, each valve plate 11 has a fan shape centered on the center of the annular channel 44.
The unfolding and convergence of the unit body 10 can be achieved by means of an existing chain drive. Specifically, the chain is located outside the annular channel 44, and the chain is enclosed into an annular shape and movably connected with the connecting rod 13, so as to drive the unit body 10 to be unfolded or converged.
According to one embodiment of the present disclosure, the valve of the present disclosure further includes an actuation ring 20 located outside the annular channel 44; the side wall of the annular channel 44 opposite the actuating ring 20 is a supporting side wall; the two ends of the valve plate 11 along the radial direction are respectively a connecting end and a sliding end; the connection end is hinged to the actuation ring 20; the sliding end and the supporting side wall are provided with a sliding connection structure; the actuating ring 20 is used for driving the valve plate 11 to be unfolded along the circumferential direction.
In the two annular channel 44 embodiment, the intermediate gate 43 is the support sidewall.
The actuating ring 20 is driven to rotate by a rotary driving piece such as a motor, and the valve plate 11 can be driven to be unfolded along the circumferential direction by the actuating ring 20, so that the unit body 10 can be unfolded and converged.
According to one embodiment of the present disclosure, the sliding connection includes an annular rib and an annular groove 14 into which the annular rib fits. The annular groove 14 may be formed in one of the sliding end and the intermediate gate 43, while the annular rib is fixed in the other.
Two hinge rods may be provided between each valve plate 11 and the actuating ring 20, one end of one hinge rod being hinged to the connection end and the other end being hinged to one end of the other hinge rod, the other end of the other hinge rod being hinged to the actuating ring 20. According to one embodiment of the present disclosure, the actuation ring 20 is provided in plurality, and the plurality of actuation rings 20 are arranged in the flow direction; the actuating ring 20 is positioned between two adjacent valve plates 11 along the flow direction; each actuating ring 20 is provided with a strip hole 21 arranged along the radial direction; a connecting rod 30 is inserted in the strip hole 21; connecting rods 13 are hinged to the connecting ends of two adjacent valve plates 11, one ends of the two connecting rods 13 are hinged to the connecting ends of the two valve plates 11 respectively, and the other ends of the two connecting rods 13 are hinged to the two ends of the connecting rod 30 respectively.
In the description of the present specification, reference to the terms "one embodiment/manner," "some embodiments/manner," "example," "a particular example," "some examples," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment/manner or example is included in at least one embodiment/manner or example of the application. In this specification, the schematic representations of the above terms are not necessarily for the same embodiment/manner or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments/modes or examples. Furthermore, the various embodiments/modes or examples described in this specification and the features of the various embodiments/modes or examples can be combined and combined by persons skilled in the art without contradiction.
Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include at least one such feature. In the description of the present application, the meaning of "plurality" means at least two, for example, two, three, etc., unless specifically defined otherwise.
It will be appreciated by those skilled in the art that the above-described embodiments are merely for clarity of illustration of the disclosure, and are not intended to limit the scope of the disclosure. Other variations or modifications will be apparent to persons skilled in the art from the foregoing disclosure, and such variations or modifications are intended to be within the scope of the present disclosure.
Claims (9)
1. A valve for an aircraft engine annular channel (44), characterized by comprising: a plurality of unit bodies (10) uniformly distributed in the circumferential direction in the annular passage (44);
each unit body (10) is of a folding fan structure and comprises a plurality of valve plates (11) distributed along the flow direction, at least one end of each valve plate (11) is hinged with a connecting rod (13), and two adjacent valve plates (11) are movably connected through at least two connecting rods (13);
the valve plate (11) is in sliding fit with the annular channel (44), and the valve plate (11) is arranged in a sliding manner along the circumferential direction;
the plurality of valve plates (11) of each unit body (10) can be unfolded along the circumferential direction and form a fan-shaped annular sealing structure;
when each unit body (10) is in an unfolding state, a plurality of fan-shaped annular sealing structures circumferentially seal the whole annular channel (44);
further comprising an actuation ring (20) located outside said annular channel (44);
the side wall of the annular channel (44) opposite to the actuating ring (20) is a supporting side wall;
the two ends of the valve plate (11) along the radial direction are respectively a connecting end and a sliding end;
the connecting end is hinged to the actuating ring (20);
the sliding end and the supporting side wall are provided with a sliding connection structure;
the actuating ring (20) is used for driving the valve plate (11) to be unfolded along the circumferential direction.
2. Valve for an aeroengine annular channel (44) according to claim 1, wherein a sealing end face (12) is provided between any adjacent two unit bodies (10); the sealing end face (12) is used for sealing a gap between two adjacent unit bodies (10) in the unfolded state.
3. A valve for an aeroengine annular channel (44) as in claim 1, wherein each of said units (10) is in the shape of a streamline along the flow direction when said units (10) are in a converging condition.
4. Valve for an aeroengine annular channel (44) according to claim 1, wherein the projected shape and projected area of each of said valve plates (11) on the same cross section of said annular channel (44) are identical.
5. Valve for an aeroengine annular channel (44) according to claim 1, wherein each of said flaps (11) has a sector-annular shape centred on the centre of the annular channel (44).
6. Valve for an aeroengine annular channel (44) according to claim 1, wherein 3-5 valve plates (11) are provided per unit body (10); and/or
3-9 unit bodies (10) are arranged in the cross section of each annular channel (44).
7. A valve for an aircraft engine annular channel (44) according to claim 1, wherein the sliding connection comprises an annular rib and an annular groove (14) in which the annular rib is fitted.
8. Valve for an aeroengine annular channel (44) according to claim 1, wherein said actuation ring (20) is provided in plurality, a plurality of said actuation rings (20) being arranged in a flow direction;
the actuating ring (20) is positioned between two adjacent valve plates (11) along the flow direction;
each actuating ring (20) is provided with a strip hole (21) arranged along the radial direction;
a connecting rod (30) is inserted in the strip hole (21);
connecting rods (13) are hinged to the connecting ends of two adjacent valve plates (11), one ends of the two connecting rods (13) are hinged to the connecting ends of the two valve plates (11) respectively, and the other ends of the two connecting rods (13) are hinged to the two ends of the connecting rod (30) respectively.
9. Valve for an aeroengine annular channel (44) according to any of claims 1 to 6, further comprising a chain outside said annular channel (44), which is looped and is movably connected to the connecting rod (13) for driving the unit (10) to open or close.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111079753.2A CN113719623B (en) | 2021-09-15 | 2021-09-15 | Valve for annular channel of aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111079753.2A CN113719623B (en) | 2021-09-15 | 2021-09-15 | Valve for annular channel of aero-engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113719623A CN113719623A (en) | 2021-11-30 |
| CN113719623B true CN113719623B (en) | 2023-09-22 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111079753.2A Active CN113719623B (en) | 2021-09-15 | 2021-09-15 | Valve for annular channel of aero-engine |
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| Country | Link |
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| CN (1) | CN113719623B (en) |
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| CN112797171A (en) * | 2021-01-27 | 2021-05-14 | 中国航发长春控制科技有限公司 | Anti-surge air-release valve structure of engine air system |
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| WO2007116319A2 (en) * | 2006-01-20 | 2007-10-18 | Rolls-Royce Power Engineering Plc | Bleed off valve system |
| US20150041695A1 (en) * | 2013-08-07 | 2015-02-12 | Kyle P. Daniels | Shutter valve |
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| CH387403A (en) * | 1962-06-02 | 1965-01-31 | Apolonius Warzynski Edward | Valve |
| CN1834513A (en) * | 2006-04-10 | 2006-09-20 | 潘世永 | Valve |
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| CN207848516U (en) * | 2018-02-08 | 2018-09-11 | 合肥富厚机电制造有限公司 | A kind of oil circuit current limiter |
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| CN111319778A (en) * | 2018-12-13 | 2020-06-23 | 空中客车运营简化股份公司 | Turbofan engine and aircraft |
| CN109404546A (en) * | 2018-12-16 | 2019-03-01 | 中国航发沈阳发动机研究所 | Sealing structure and design method in a kind of engine mode selection mechanism |
| CN111470051A (en) * | 2019-01-24 | 2020-07-31 | 空中客车运营简化股份公司 | Turbofan engine and aircraft |
| CN111731488A (en) * | 2019-03-25 | 2020-10-02 | 空中客车运营简化股份公司 | Turbofan including a set of rotatable blades for blocking a bypass flow duct |
| CN111828199A (en) * | 2019-04-15 | 2020-10-27 | 空中客车运营简化股份公司 | Turbofan engine and aircraft |
| CN112797171A (en) * | 2021-01-27 | 2021-05-14 | 中国航发长春控制科技有限公司 | Anti-surge air-release valve structure of engine air system |
Also Published As
| Publication number | Publication date |
|---|---|
| CN113719623A (en) | 2021-11-30 |
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