CN103847968A - Novel wing icing prevention system using airborne waste heat - Google Patents

Abstract

The invention discloses a novel wing anti-icing system utilizing airborne waste heat. The system realizes the connection of a skin heat exchanger, a rotor compressor, an evaporator and an electronic expansion valve through pipelines. A liquid reservoir was added in the wing anti-icing cavity, and the structure of the double skin was changed. The system of the present invention adopts the evaporative cycle anti-icing method on the UAV, uses the evaporative heat exchanger components to fully absorb the heat source heat of the airborne electronic equipment, and transfers the heat to the skin and the outside world through the impact of the flute tube. The cold and humid air conducts heat exchange to increase the skin temperature to the lowest anti-icing temperature to achieve the anti-icing effect.

Description

A New Wing Anti-icing System Utilizing Airborne Waste Heat

technical field

The present invention relates to an anti-icing system of an aircraft, more particularly, refers to a novel wing anti-icing system utilizing airborne waste heat.

Background technique

Modern aircraft, especially unmanned aircraft, use a large number of various electronic components and electronic equipment, resulting in high local heat generation. If effective heat dissipation is not carried out, the performance of electronic equipment will be seriously reduced, and heat dissipation treatment must be carried out. When an aircraft passes through clouds containing supercooled water droplets, many components may freeze, such as wings, leading edges of the empennage, propellers, helicopter rotor blades, engine air intakes, pitot tubes, windshields, etc. The large-scale UAV is the current development trend. The flying height, speed and flight time of large-scale UAVs have been greatly improved, thus entering the icing envelope to generate icing.

Contents of the invention

In order to solve the defect that a large number of engine bleed air is used in the current wing hot air anti-icing system, resulting in insufficient engine thrust, the present invention proposes a new wing anti-icing system utilizing airborne waste heat. The system of the present invention has inherent advantages in anti-icing on unmanned aerial vehicles. It adopts the anti-icing method of evaporative circulation, uses the evaporative heat exchanger components to fully absorb the heat source heat of the airborne electronic equipment, and impacts the jet flow through the flute tube. The heat is transferred to the skin to exchange heat with the supercooled and humid air outside, and the temperature of the skin is increased to the lowest anti-icing temperature to achieve the anti-icing effect. During the wing anti-icing process, the system of the present invention makes full use of the waste heat of electronic equipment, lubricating oil, and hydraulic oil that should be dissipated on the aircraft, and does not need to carry a cold source, nor does it need to bleed air or electric heating from the engine, saving a lot of energy. Bleed air, which increases engine thrust.

The present invention is a novel wing anti-icing system utilizing airborne waste heat, the system includes a skin heat exchanger (1), a rotor compressor (2), an evaporator (3) and an electronic expansion valve (4) ;

The skin heat exchanger (1) is communicated with the rotary compressor (2) through a second pipeline (5B);

The third pipe (5C) is used to communicate between the skin heat exchanger (1) and the electronic expansion valve (4);

The evaporator (3) is communicated with the rotary compressor (2) through a first pipeline (5A);

The evaporator (3) communicates with the electronic expansion valve (4) through a fourth pipe (5D).

The present invention is a novel wing anti-icing system utilizing airborne waste heat. In the system, the first pipe (5A) flows dry saturated steam; the second pipe (5B) flows with a temperature not lower than 100 ℃ high-temperature hot steam; the third pipeline (5C) flows a cooled saturated liquid whose temperature is not higher than 20℃; the fourth pipeline (5D) flows a cooled liquid.

The present invention utilizes the advantage of the novel wing anti-icing system of airborne waste heat to be:

①A closed circulation system of the present invention is composed of four passages, a skin heat exchanger 1, a rotor compressor 2, an evaporator 3 and an electronic expansion valve 4, which can be used flexibly, and the heat source can be fully used when the heat source generates a large amount of heat The heat is used for anti-icing; when the heat of the heat source is low, the work of the compressor can be increased to supplement the heat flow required for anti-icing.

2. The required parts of the system of the present invention are simple in structure, and a liquid reservoir is added to the existing wing structure to improve the double-skin structure; an electronic expansion valve 4 is set on the third pipeline 5C to expand and cool down; the rotor compressor 2 is used The pressure provided makes the system channels circulatory.

③ The system of the present invention utilizes four channels to form a closed cycle, which effectively reduces the complexity of the existing anti-icing system.

④The system of the present invention does not need to bleed air from the engine, which reduces engine gas consumption and improves engine thrust.

⑤ The system of the present invention utilizes on-board equipment and heating components as the cold source of the evaporation end, effectively utilizes the waste heat on the machine, saves energy, and thus realizes the evaporative cycle process.

Description of drawings

Fig. 1 is a structural block diagram of a novel wing anti-icing system utilizing airborne waste heat according to the present invention.

Fig. 2 is the anti-icing structural diagram of the wing skin heat exchanger of the present invention.

Fig. 2A is another view of the anti-icing structure of the wing skin heat exchanger of the present invention.

Fig. 2B is an exploded view of the anti-icing structure of the wing skin heat exchanger of the present invention.

FIG. 2C is a sectional view along line A-A of FIG. 2 .

Fig. 2D is a partially enlarged view of Fig. 2C.

Fig. 3 is a structural diagram of the double skin structure in the wing skin heat exchanger of the present invention.

Fig. 4 is a structural diagram of the liquid reservoir in the wing skin heat exchanger of the present invention.

Fig. 4A is another structural view of the liquid reservoir in the wing skin heat exchanger of the present invention.

FIG. 4B is a cross-sectional view along line A-A of FIG. 4 .

1. Skin heat exchanger 1A. Wing skin 2. Rotary compressor 3. Evaporator 4. Electronic expansion valve 5A. Dry saturated cold steam piping 5B. High temperature and high pressure hot steam pipeline 5C. Saturated liquid pipeline after cooling 5D. Cooling and depressurizing wet liquid pipeline 6. Wing 6B.A support plate 6B. Piano tube 6B1. Nozzle 6B2. Steam distribution pipe 6C.B support plate 7. Double skin structure 7A. Skin matrix 7B. Arc limit 7C.C support plate 7D. Through cavity 7E. Raised 7F.D support plate 8. Reservoir 8A. Limit slot 8B. Pumping hole 9. Anti-icing cavity

Detailed ways

The present invention will be further described in detail below in conjunction with the accompanying drawings.

Referring to shown in Fig. 1, the present invention provides a kind of novel airfoil anti-icing system utilizing airborne waste heat, and this system comprises four parts, is skin heat exchanger 1, rotor compressor 2, evaporator 3 and electronics respectively. Expansion valve 4;

The skin heat exchanger 1 and the rotary compressor 2 are communicated through a second pipeline 5B; high-temperature hot steam flows in the second pipeline 5B; the temperature is not lower than 100°C;

A third pipe 5C is used to communicate between the skin heat exchanger 1 and the electronic expansion valve 4; the third pipe 5C flows a cooled saturated liquid; the temperature is not higher than 20°C;

The evaporator 3 communicates with the rotary compressor 2 through a first pipeline 5A; what flows in the first pipeline 5A is dry saturated steam;

The evaporator 3 communicates with the electronic expansion valve 4 through a fourth pipeline 5D; the cooled liquid flows in the fourth pipeline 5D.

In the present invention, the first pipe 5A, the second pipe 5B, the third pipe 5C and the fourth pipe 5D are pure copper pipes with a diameter of 5-15 mm.

In the present invention, the skin heat exchanger 1 may adopt the anti-icing form of piccolo tubes.

In the present invention, the rotor-type compressor 2 is a rotor-type R222V44W3853P cooling and heating type compressor produced by Panasonic Corporation, with a cooling capacity of 8000W. The evaporator 3 selects the CB77 plate evaporator produced by TRANE Trane Company. The electronic expansion valve 4 selects the ETS12.5 electronic expansion valve produced by Danfoss, with a power of 57KW.

The novel wing anti-icing system designed by the present invention utilizes the waste heat generated by the electronic equipment in the drone according to the following principles:

(A) The heat generated by the electronic equipment and components in the UAV is called the heat source of the system of the present invention, and the heat generated by the heat source is recorded as Q _s ;

(B) After the heat Q _s is transferred to the evaporator 3, the refrigerant in the evaporator 3 absorbs the heat Q _s and undergoes a phase change, so that the heat Q _s becomes dry saturated steam steam ₃ . The vapor steam ₃ is transmitted to the rotary compressor 2 through the first pipeline 5A;

(C) The dry saturated steam steam ₃ is sucked into the rotor compressor 2 under negative pressure, compressed into a high-temperature and high-pressure superheated gas steam ₂ after passing through the rotor compressor 2, and the steam ₂ is transmitted to the skin through the second pipeline 5B heat exchanger 1;

(D) The skin heat exchanger 1 fully exchanges heat with the outside world to achieve the purpose of wing anti-icing. After the steam ₂ is cooled by the skin heat exchanger 1, it condenses into a saturated liquid surface ₁ , and the surface ₁ passes through the third pipeline 5C transmitted to the electronic expansion valve 4;

(E) After the surface ₁ passes through the electronic expansion valve 4, it becomes steam ₄ with low dryness after cooling down and depressurizing after expansion, and the steam ₄ is transmitted to the evaporator 3 through the fourth pipeline 5D, thus completing an unmanned aerial vehicle The waste heat from the wings utilizes a closed-loop anti-icing system.

The novel wing anti-icing system designed by the present invention is an evaporative cycle design, and its energy conservation relationship is:

Since the system of the present invention is a closed-loop system, there is no material exchange with the outside world, and there are only two forms of energy transfer: heat and work, so the energy conservation relationship is expressed as Q ₁ =P ₂ +Q ₃ -Q _L .

Q_n为防冰热负荷，单位kW，η₁为蒙皮换热器的换热效率；Q ₁ is the heat transfer capacity that the skin heat exchanger can achieve, and

Q _n is the anti-icing heat load, unit kW, and η ₁ is the heat transfer efficiency of skin heat exchanger;

Q ₃ is the heat exchange that the evaporator can achieve;

P ₂ is the effective power of the compressor, and P ₂ =P×η ₂ , P is the rated power of the compressor, the unit is kW, and η ₂ is the effective efficiency of the compressor; the selection of the rotary compressor model is based on the evaporation of the evaporator The temperature T _eva , the skin anti-icing cavity condensation temperature T _con and the system cooling load Q _s are determined.

Q _L is the heat loss of the system pipeline, that is, the heat loss on the first pipeline 5A, the second pipeline 5B, the third pipeline 5C and the fourth pipeline 5D, and the unit is kW.

In the present invention, the heat exchange capacity of the evaporator is Q ₂ =Q _s ×η ₃ , Q _s =∑Q _i , η ₃ is the heat exchange efficiency of the evaporator, Q _s is the heat source heat of the system, and Q _i is the on-board demand Heat flow for heat dissipation, such as heat-generating electronic equipment, lubricating oil, etc.

According to the various heat flows in the external icing environment, the heat load _Qn required for anti-icing is calculated as:

Q _n ＝∑(q _a +q _v +q _e +q _w +q _wv )×A

where A is the heat transfer area; q _a specific heat flow for convective heat transfer; q _v the specific heat flow for heating the surface due to the air flow caused by the friction of the boundary layer; q _e the specific heat flow required for water evaporation on the surface; q _w heats the collected water droplets specific heat flow; q _wv water droplet kinetic energy converted into specific heat flow, the unit is kW/m ² .

In the present invention, the skin heat exchanger 1 includes a winged skin 1A, a flute tube 6B, a double-skin structure 7 , an A support plate 6A, a B support plate 6C, and a liquid reservoir 8 .

Wing Skin 1A

Referring to Fig. 2, Fig. 2A, Fig. 2B, Fig. 2C, and Fig. 2D, the wing skin 1A is an airfoil structure processed by aluminum alloy material. The inner wall of the wing skin 1A, the double skin structure 7 and the liquid reservoir 8 form an anti-icing cavity 9 . The hot steam ejected from the nozzle hole 6B1 of the flute pipe 6B impinges on the inner wall of the leading edge of the wing skin 1A, and then diffuses along the direction of the arrow. The hot steam diffused in the anti-icing chamber 9 enters the storage tank after being cooled. In the liquid container 8. The temperature of the hot steam injected from the nozzle hole 6B1 of the piccolo 6B is generally not lower than 100°C. The temperature of the hot steam after passing through the anti-icing chamber 9 is generally not higher than 20°C.

Piccolo 6B

Referring to Fig. 2, Fig. 2B, Fig. 2C, and Fig. 2D, one end of the flute pipe 6B is connected to one end of the steam distribution pipe 6B2, and the other end of the steam distribution pipe 6B2 is connected to one end of the second pipeline 5B, and the second pipeline 5B The other end is connected with the outlet port of the rotary compressor 2. An injection hole 6B1 is provided on the flute tube 6B. In the present invention, the nozzle holes 6B1 on the flute tube 6B are distributed in arrays, and multiple arrays can be arranged in parallel or forked rows on the circumference of the flute tube 6B.

Double skin structure 7

Referring to FIG. 2B , FIG. 2C , FIG. 2D , and FIG. 3 , the middle part of the double-skin structure 7 is a cavity 7D, which is used to reduce the weight of the double-skin structure 7 . The base 7A of the double-skinned structure 7 is provided with an arc-shaped limiter 7B and a protrusion 7E. The arc-shaped limiter 7B is matched with the flute-shaped tube 6B to realize the heat ejected from the nozzle hole 6B1 of the flute-shaped tube 6B. Vapor flows along the curved walls. The protrusion 7E is installed in the limiting groove 8A of the liquid reservoir 8 . Both ends of the double-skinned structure 7 are respectively provided with a C support plate 7C and a D support plate 7F.

A support plate 6A

Referring to FIG. 2 and FIG. 2B , the A support plate 6A is arranged at one end of the skin heat exchanger 1 .

B support plate 6C

Referring to FIG. 2A and FIG. 2B , the B supporting plate 6C is arranged at the other end of the skin heat exchanger 1 .

Reservoir 8

Referring to FIG. 2B , FIG. 2C , FIG. 2D , FIG. 4 , FIG. 4A , and FIG. 4B, the liquid reservoir 8 has a T-shaped cavity structure inside. One side plate of the liquid reservoir 8 is provided with a limiting groove 8A, which is used to place the protrusion 7E of the double-skin structure 7; Hole 8B, the pumping hole 8B is connected to one end of the third pipe 5C, the other end of the third pipe 5C is connected to the inlet of the electronic expansion valve 4, and the pumping hole 8B is used to condense the cooled condensate in the T-shaped cavity into Saturated liquid is discharged to realize heat exchange. The inside of the liquid reservoir 8 is provided with a T-shaped partition 8E, which divides the cavity inside the liquid reservoir 8 into a first chamber 8C and a second chamber 8D, and the T-shaped partition 8E is provided with The communication hole 8F (in order to clearly enlarge the communication hole and show it with a dotted line), the condensed saturated liquid in the first chamber 8C enters the second chamber 8D through the communication hole 8F, and the condensed saturated liquid in the second chamber 8D is pumped Orifice 8B (shown with dotted lines enlarged for clarity) enters third conduit 5C.

The novel airfoil anti-icing system designed by the present invention using airborne waste heat uses four channels to connect with the skin heat exchanger 1, the rotor compressor 2, the evaporator 3 and the electronic expansion valve 4 to form a closed cycle. Anti-icing system. It is flexible to use. When the heat source generates a large amount of heat, the heat of the heat source can be fully used for anti-icing; when the heat of the heat source is small, the work of the compressor can be increased to supplement the heat flow required for anti-icing.

Claims (6)

1. a novel wing anti-ice system that utilizes airborne used heat, is characterized in that: this system includes covering heat exchanger (1), rotor-type compressor (2), evaporator (3) and electric expansion valve (4);

Between covering heat exchanger (1) and rotor-type compressor (2), adopt second pipe (5B) to be communicated with;

Between covering heat exchanger (1) and electric expansion valve (4), adopt the 3rd pipeline (5C) to be communicated with;

Between evaporator (3) and rotor-type compressor (2), adopt the first pipeline (5A) to be communicated with;

Between evaporator (3) and electric expansion valve (4), adopt the 4th pipeline (5D) to be communicated with.

2. the novel wing anti-ice system that utilizes airborne used heat according to claim 1, is characterized in that: what in described the first pipeline (5A), flow is dry saturated steam; What in described second pipe (5B), flow is that temperature is not less than the high temperature vapours of 100 ℃; What flow in described the 3rd pipeline (5C) is that temperature is not higher than the cooling saturated liquid of 20 ℃; What in described the 4th pipeline (5D), flow is the liquid after cooling.

3. the novel wing anti-ice system that utilizes airborne used heat according to claim 1, is characterized in that: the first pipeline (5A), second pipe (5B), the 3rd pipeline (5C) and the 4th pipeline (5D) are pure copper tube, and diameter is 5～15mm.

4. the novel wing anti-ice system that utilizes airborne used heat according to claim 1, is characterized in that: covering heat exchanger (1) includes wing cover (1A), bourdon's tube (6B), two stressed-skin construction body (7), A stay bearing plate (6A), B stay bearing plate (6C), reservoir (8);

The inwall of wing cover (1A) forms anti-icing chamber (9) with two stressed-skin construction bodies (7), reservoir (8); The leading edge inwall that the heat steam punching of ejecting from the spray orifice (6B1) of bourdon's tube (6B) is mapped to wing cover (1A), then spreads along the direction of arrow, and the heat steam being diffused in anti-icing chamber (9) enters in reservoir (8) after cooling;

Bourdon's tube (6B) is provided with spray orifice (6B1); One end of bourdon's tube (6B) is connected with one end of steam distribution pipe (6B2), and the other end of steam distribution pipe (6B2) is connected with one end of second pipe (5B), and the other end of second pipe (5B) is connected with the exit end of rotor compressor (2);

The middle part of two stressed-skin construction bodies (7) is cavity (7D), the matrix (7A) of two stressed-skin construction bodies (7) is provided with arc-shaped limit (7B), projection (7E), this arc-shaped limit (7B) mates with bourdon's tube (6B), realizes the heat steam ejecting and flow along arcwall from the spray orifice (6B1) of bourdon's tube (6B); This projection (7E) is arranged in the position-limited trough (8A) of reservoir (8); The two ends of two stressed-skin construction bodies (7) are respectively equipped with C stay bearing plate (7C), D stay bearing plate (7F);

A stay bearing plate (6A) is arranged on one end of covering heat exchanger (1), and B stay bearing plate (6C) is arranged on the other end of covering heat exchanger (1);

Reservoir (8) is that inside is T shape cavity structure; The side plate face of reservoir (8) is provided with position-limited trough (8A), and this position-limited trough (8A) is for placing the projection (7E) of two stressed-skin construction bodies (7); Another lateral plates of reservoir (8) is provided with drawing liquid hole (8B), and drawing liquid hole (8B) is connected with one end of the 3rd pipeline (5C); The inside of reservoir (8) is provided with T-shaped dividing plate (8E), and the inner cavity of reservoir (8) is divided into the first chamber (8C) and the second chamber (8D) by described T-shaped dividing plate (8E), and T-shaped dividing plate (8E) is provided with intercommunicating pore (8F).

5. the novel wing anti-ice system that utilizes airborne used heat according to claim 4, is characterized in that: the spray orifice (6B1) on bourdon's tube (6B), for display distributes, can arrange multiple displays according to in-line arrangement or fork row on the circumference of bourdon's tube (6B).

6. the novel wing anti-ice system that utilizes airborne used heat according to claim 1, is characterized in that used heat utilizes principle to be:

(A) in unmanned plane, electronic machine and components and parts are called the thermal source of system of the present invention as the heat producing, and the heat that this thermal source produces is designated as Q _s;

(B) described heat Q _spass to after evaporator 3, absorb described heat Q via the refrigerant in evaporator 3 _safter undergo phase transition, make described heat Q _sbecome dry saturation vapor steam ₃, this dry saturation vapor steam ₃be transferred to rotor-type compressor 2 through the first pipeline 5A;

(C) described dry saturation vapor steam ₃under negative pressure, be inhaled in rotor compressor 2, after rotor compressor 2, be compressed into the overheated gas steam of High Temperature High Pressure ₂, this steam ₂be transferred to covering heat exchanger 1 through second pipe 5B;

(D) covering heat exchanger 1 fully reaches the anti-icing object of wing, described steam with extraneous heat-shift ₂after covering heat exchanger 1 is cooling, be condensed into saturated liquid surface ₁, this surface ₁be transferred to electric expansion valve 4 through the 3rd pipeline 5C;

(E) described surface ₁after electric expansion valve 4, become the damp steam steam of low mass dryness fraction by decrease temperature and pressure after expanding ₄, this steam ₄be transferred to evaporator 3 through the 4th pipeline 5D, thereby the used heat that completes a unmanned plane wing utilizes the anti icing system of closed cycle.

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