Anti-icing air bleed method and structure

Abstract

The present invention discloses an anti-icing air bleed method and structure, wherein the method includes introducing high-temperature and high-pressure gas in the compressor flow channel into the rotor inner cavity, the high-temperature and high-pressure gas flows in the rotor inner cavity to the front end of the rotor, and is led out through the air outlet at the front end of the rotor, the high-temperature gas enters the internal air cavity of the guide vane through the air inlet at the lower end of the adjustable guide vane, and the led-out gas enters the support plate air cavity or the front end air intake cone cavity through the internal air bleed channel of the supporting casing. The structure includes a rear end air bleed hole at the rear end blade disk drum structure of the rotor, a front end air outlet at the front end journal structure of the rotor, and an air inlet is arranged at the lower end of the adjustable guide vane. The present invention does not need to open an air bleed duct inside the engine, but only needs to open an opening on the corresponding component, thereby solving the technical problem of leading the high-temperature gas at the rear end of the engine to the front end air intake cone and the adjustable guide vane.

Description

Technical Field

[0001] The invention belongs to the technical field of aeroengines, and in particular relates to an anti-icing air bleed method and structure. Background Art

[0002] When an aircraft engine is running at high altitude, the intake cone, adjustable guide vanes and other cold-end parts at the front of the engine are prone to icing due to the low outside temperature at high altitude, which affects the working stability of the engine. The current practice is usually to use bleed air interfaces, external pipelines, gas collecting cavities and other structures to guide the high-temperature gas at the rear end of the engine to the front end to heat the cold-end parts and prevent icing. This practice requires additional bleed air interfaces, external pipelines, gas collecting cavities and other structures, which increases the number and weight of engine parts.

[0003] The existing external pipeline air bleed structure requires additional air bleed interfaces, external pipelines, air collecting chambers and other structures, which increases the number and weight of engine parts. The additional parts will also occupy the external space of the engine, increasing the difficulty of laying out the engine's external pipeline lubricating oil and fuel. Summary of the invention

[0004] The object of the present invention is to provide an anti-icing air bleed method and structure, which can provide anti-icing air bleed for the intake cone and adjustable guide vane cold end parts at the front end of the engine by changing the air bleed structure inside the engine, so as to solve the problems raised in the above background technology.

[0005] To achieve the above object, the present invention provides the following technical solution: an anti-icing air bleed method, the anti-icing air bleed method comprising the following steps:

[0006] The high-temperature and high-pressure gas in the compressor flow passage is introduced into the rotor inner cavity, and the high-temperature and high-pressure gas flows toward the front end of the rotor in the rotor inner cavity;

[0007] High-temperature and high-pressure gas is drawn out from the front end of the rotor and enters the air cavity inside the adjustable guide vane from the adjustable guide vane air inlet for heating and anti-icing;

[0008] The high-temperature and high-pressure gas is introduced into the support plate air cavity or the front air intake cone cavity through the internal air bleed channel of the supporting casing for heating and anti-icing.

[0009] Preferably, the high-temperature and high-pressure gas flows in the inner cavity of the rotor toward the journal at the front end of the rotor, and is led out through the gas outlet at the front end of the rotor.

[0010] Preferably, the high-temperature and high-pressure gas in the compressor flow channel is introduced into the rotor inner cavity from the rear end of the rotor to form a blade disk with air inlet holes, and the high-temperature and high-pressure gas in the compressor flow channel is introduced into the rotor inner cavity.

[0011] Preferably, the high-temperature and high-pressure gas enters the internal air cavity of the guide vane through the air inlet at the lower end of the adjustable guide vane, and heats the adjustable guide vane to prevent icing.

[0012] Preferably, the high-temperature and high-pressure gas fills the inner cavity of the rotor and flows forward, and the high-temperature and high-pressure gas is led out through the gas outlet at the front end of the rotor, and the lead-out position is sealed by the comb teeth.

[0013] The present invention further proposes an anti-icing air bleed structure, which is applied to an anti-icing air bleed method. The anti-icing air bleed structure comprises:

[0014] The rotor inner cavity air induction structure has a rear end air induction hole at the rear end blade disk drum structure of the rotor, a front end air outlet at the front end journal structure of the rotor, and an air inlet at the lower end of the adjustable guide vane.

[0015] Preferably, a rear end air inlet hole is opened at the drum structure of the rotor rear end blade disk to form a blade disk with an air inlet hole, so as to introduce the high temperature and high pressure gas in the compressor flow channel into the rotor inner cavity.

[0016] Preferably, the blade disk and the rear compressor flow passage are sealed by comb teeth.

[0017] Preferably, the front air outlet lead-out position is sealed by comb teeth.

[0018] Preferably, the joint between the rotor and the stator is sealed with comb teeth.

[0019] Preferably, the rotor comprises: a compressor disc, a comb disc and a pull rod; wherein the compressor disc, the comb disc and the pull rod are fixedly connected; the stator comprises a comb bushing, and the comb bushing and the comb disc are sealed by the comb teeth.

[0020] Technical effects and advantages of the present invention:

[0021] The present invention can provide anti-icing bleed air for cold end parts such as the intake cone and adjustable guide vanes at the front end of the engine by changing the bleed air structure inside the engine. The present invention does not need to open a bleed air duct inside the engine. The bleed air structure involved is simple and all inside the engine, avoiding the use of external interfaces, external pipelines, external air collection structures, etc., which can effectively reduce the number of engine parts and is conducive to engine weight reduction design and external lubricating oil and fuel method layout.

[0022] Other features and advantages of the present invention will be described in the following description, and part of them will become obvious from the description, or will be understood by practicing the present invention. The purpose and other advantages of the present invention can be realized and obtained by the structures pointed out in the description, claims and drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 This is a diagram of the overall anti-icing air bleed structure of the rotor inner cavity air bleed form of the present invention;

[0024] Figure 2 The rear end structure diagram of the rotor for introducing air into the inner cavity of the rotor of the present invention;

[0025] Figure 3 The front end structure diagram of the rotor for introducing air into the inner cavity of the rotor of the present invention;

[0026] Figure 4 This is a diagram of the air path structure of the guide vanes for introducing air into the inner cavity of the rotor of the present invention;

[0027] Figure 5 The structure diagram of the support plate gas path for introducing air into the inner cavity of the rotor of the present invention;

[0028] Figure 6 This is a structural diagram of the air path of the air intake cone for introducing air into the inner cavity of the rotor of the present invention;

[0029] In the figure: 1-rear end air inlet; 2-blade disk; 3-guide vane air inlet; 4-adjustable guide vane; 5-support casing; 6-support plate; 7-intake cone; 8-front end air outlet. DETAILED DESCRIPTION

[0030] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0031] The present invention provides an anti-icing air bleed method, comprising the following steps:

[0032] The high-temperature and high-pressure gas in the compressor flow passage is introduced into the rotor inner cavity, and the high-temperature and high-pressure gas flows toward the front end of the rotor in the rotor inner cavity;

[0033] High-temperature and high-pressure gas is drawn out from the front end of the rotor and enters the air cavity inside the adjustable guide vane 4 from the air inlet of the adjustable guide vane 4 for anti-icing air bleed;

[0034] The high-temperature and high-pressure gas introduced enters the air cavity of the support plate 6 or the front air intake cone cavity through the internal air introduction channel of the supporting casing 5 for anti-icing air introduction.

[0035] Specifically, a rear end air inlet hole 1 is opened at the drum structure of the rotor rear end blade disk 2 to form a blade disk 2 with an air inlet hole, so as to introduce the high-temperature and high-pressure gas in the compressor flow channel into the rotor inner cavity; at the same time, the high-temperature and high-pressure gas fills the rotor inner cavity and flows forward, and is led out through the air outlet at the front end of the rotor, and the lead-out position is sealed by the grate teeth; and the high-temperature gas enters the internal air cavity of the guide vane through the air port at the lower end of the adjustable guide vane 4, so as to heat and prevent icing of the adjustable guide vane 4; at the same time, the led-out gas is led to the front end air intake cone cavity through the internal air inlet channel of the supporting casing 5, so as to heat and prevent icing of the air intake cone 7.

[0036] In this embodiment, the high-temperature and high-pressure gas flows in the inner cavity of the rotor toward the journal at the front end of the rotor, and is led out through the gas outlet at the front end of the rotor.

[0037] In this embodiment, the high-temperature and high-pressure gas in the compressor flow channel is introduced into the rotor inner cavity from the rear end of the rotor, wherein a rear end air inlet hole 1 is opened at the drum structure of the rotor rear end blade disk 2 to form a blade disk 2 with an air inlet hole, so as to introduce the high-temperature and high-pressure gas in the compressor flow channel into the rotor inner cavity.

[0038] The anti-icing air bleed method mainly guides the high-temperature gas at the rear end of the engine to the front intake cone 7 and the adjustable guide vane 4. The air bleed structure involved in the present invention is simple and is all inside the engine, avoiding the use of external interfaces, external pipelines, external air collection structures, etc., which can effectively reduce the number of engine parts and is conducive to the weight reduction design of the engine and the layout of external lubricating oil and fuel methods.

[0039] The present invention further provides an anti-icing air bleed structure, which is applied to the above-mentioned anti-icing air bleed method, wherein the anti-icing air bleed structure comprises:

[0040] A rear air inlet 1 is provided at the drum structure of the rear end blade disk 2 of the rotor, a front air outlet 8 is provided at the front end journal structure of the rotor, and an air inlet is provided at the lower end of the adjustable guide vane 4.

[0041] The rear end blade disk 2 of the rotor has a rear end air inlet hole 1 at its drum structure, forming a blade disk 2 with an air inlet hole, so as to introduce high temperature and high pressure gas in the compressor flow passage into the rotor inner cavity.

[0042] A front end gas outlet 8 is provided at the front end journal structure of the rotor for leading high temperature and high pressure gas out from the front end of the rotor.

[0043] The lower end of the adjustable guide vane 4 is provided with an air inlet for introducing high-temperature and high-pressure gas from the air inlet of the adjustable guide vane 4 into the internal air cavity of the adjustable guide vane 4 to perform anti-icing and air inlet on the adjustable guide vane 4 .

[0044] Next, a detailed description will be given in conjunction with specific embodiments.

[0045] When the engine size is small, the rotor cavity air bleed form is selected. The rotor cavity air bleed includes introducing the high-temperature and high-pressure gas in the compressor flow channel into the rotor cavity from the rear end air bleed hole 1, and the high-temperature and high-pressure gas flows in the rotor cavity to the shaft neck at the front end of the rotor, and is led out through the rotor front end air outlet 8, and the high-temperature gas enters the internal air cavity of the guide vane through the air inlet at the lower end of the adjustable guide vane 4, and the led-out gas enters the air cavity of the support plate 6 or the front end air intake cone cavity through the internal air bleed channel of the supporting casing 5.

[0046] Correspondingly, the anti-icing air bleed structure includes a rear end air bleed hole 1 opened at the drum structure of the rear end blade disk 2 of the rotor, a front end air outlet 8 opened at the front end journal structure of the rotor, and the connection between the rotor and the stator is sealed with comb teeth.

[0047] Specifically, the rotor comprises: a final compressor disc, a grate disc and a tie rod; wherein the final compressor disc, the grate disc and the tie rod are fixedly connected; and the end of the grate disc is provided with oblique grate teeth;

[0048] The stator comprises: a comb tooth bushing and a combustion chamber inner ring, wherein the comb tooth bushing is fixedly connected to the combustion chamber inner ring;

[0049] The following is a detailed description with reference to the accompanying drawings. Figure 1 As shown, a rear end air inlet hole 1 is opened at the drum structure of the blade disk 2 at the rear end of the engine, and a blade disk 2 with an air inlet hole is formed at the rear end of the rotor to introduce the high-temperature and high-pressure gas in the compressor flow channel into the rotor inner cavity. The high-temperature and high-pressure gas fills the rotor inner cavity and flows forward. A front end air outlet 8 is opened at the rotor front end journal structure, and a front journal with an air outlet is formed at the front end of the rotor. The high-temperature and high-pressure gas flows in the rotor inner cavity to the journal at the front end of the rotor and is led out through the air outlet at the front end of the rotor. At the same time, the lead-out position can be sealed by comb teeth. The adjustable guide vane 4 is provided with an air inlet at the bottom end thereof, and the high-temperature gas drawn out from the air outlet enters into the internal air cavity of the guide vane through the air inlet at the lower end thereof, so as to heat and prevent icing of the adjustable guide vane 4; the joint between the rotor and the stator may be sealed with comb teeth, and the drawn-out gas may enter into the air cavity of the support plate 6 through the internal air inlet channel of the supporting casing 5, so as to heat and prevent icing of the support plate 6; the gas may also be drawn to the cavity of the front air intake cone 7 through the internal air intake channel of the supporting casing 5, so as to heat and prevent icing of the air intake cone 7.

[0050] In this embodiment, the structure of the rear end of the rotor is as follows: Figure 2 As shown, the compressor includes a rotating part and a stator part, and the rotor part includes: a compressor disk, a comb tooth disk and a tie rod; wherein the last stage compressor disk, the comb tooth disk and the tie rod are fixedly connected. An air bleed port is provided between the top disk and the drum of the compressor disk, and the high-temperature and high-pressure airflow enters the blade disk 2 from the air bleed port. The stator part includes: a comb tooth bushing, and the comb tooth bushing and the comb tooth disk are sealed by the comb teeth.

[0051] A rear air inlet hole 1 is provided on the rear blade disk 2 of the engine rotor, and the high-temperature and high-pressure gas in the compressor flow passage is introduced into the rotor cavity through the air inlet hole. The blade disk 2 is an irregular cross shape, and the blade disk 2 and the rear compressor flow passage are sealed by grate teeth.

[0052] In this embodiment, the rotor front end structure is as follows: Figure 3As shown, a front air outlet 8 is opened at the front end journal structure of the rotor, and a front journal with an air outlet is formed at the front end of the rotor. The high-temperature and high-pressure gas flows to the journal at the front end of the rotor in the inner cavity of the rotor, and is led out through the outlet hole at the front end of the rotor. At the same time, the lead-out position can be sealed by the grate teeth. The grate tooth sealing includes a plurality of stepped beveled grate teeth designed on the grate tooth disc, the number of steps is 2 to 3, the step height is about 1 / 3 to 2 / 3 of the tooth height, and there is a honeycomb wear-resistant coating and inter-tooth grooves on the bushing that matches the grate teeth, the groove length is about 1 to 2.5 mm, and the depth is about 0.2 to 0.4 mm. The lower end of the grate tooth bushing 1 is set to a step shape, and for each step, the beveled grate tooth 1 is also set to a step shape accordingly.

[0053] In this embodiment, the guide vane gas path is as follows Figure 4 As shown, the bottom end of the adjustable guide vane 4 is provided with a guide vane air inlet 3, and the high-temperature gas enters the internal air cavity of the guide vane through the guide vane air inlet 3 at the bottom end of the adjustable guide vane 4 to heat and prevent icing of the adjustable guide vane 4. The joint between the rotor and the stator can be sealed with a comb tooth seal, specifically, the joint between the compressor disk and the comb tooth bushing is sealed with a comb tooth seal.

[0054] In this embodiment, the gas path structure of the support plate 6 is as follows: Figure 5 As shown, the induced gas enters the air cavity of the support plate 6 through the internal air bleed channel of the supporting casing 5, and heats the support plate 6 to prevent ice.

[0055] In this embodiment, the air path structure of the air intake cone 7 is as follows: Figure 6 As shown, the high-temperature and high-pressure gas is led from another route to the front air intake cone cavity through the internal air intake channel of the supporting casing 5 to heat the air intake cone 7 and prevent ice.

[0056] In summary, the present invention can provide anti-icing bleed air for cold end parts such as the intake cone 7 and adjustable guide vanes at the front end of the engine by changing the bleed air structure inside the engine. The bleed air structure involved in the present invention is simple and is all inside the engine, avoiding the use of external interfaces, external pipelines, external air collection structures, etc., which can effectively reduce the number of engine parts and is conducive to engine weight reduction design and external lubricating oil and fuel method layout.

[0057] Finally, it should be noted that the above is only a preferred embodiment of the present invention and is not intended to limit the present invention. Although the present invention has been described in detail with reference to the aforementioned embodiments, it is still possible for those skilled in the art to modify the technical solutions described in the aforementioned embodiments or to make equivalent substitutions for some of the technical features therein. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. An anti-icing air bleed method, characterized in that: The following steps are involved: The high-temperature and high-pressure gas in the compressor flow passage is introduced into the rotor cavity, wherein a rear end air inlet hole (1) is opened at the drum structure of the rotor rear end blade disk (2), and the high-temperature and high-pressure gas in the compressor flow passage is introduced into the rotor cavity through the air inlet hole (1) on the blade disk (2), and the high-temperature and high-pressure gas flows to the front end of the rotor in the rotor cavity; the high-temperature and high-pressure gas is drawn out from the front end of the rotor, and enters the internal air cavity of the adjustable guide vane (4) from the air inlet of the adjustable guide vane (4) for heating and anti-icing; the drawn high-temperature and high-pressure gas enters the air cavity of the support plate (6) or the front end air inlet cone cavity through the internal air inlet channel of the support casing (5) for heating and anti-icing.

2. An anti-icing air bleed method according to claim 1, characterized in that: The high-temperature and high-pressure gas flows in the inner cavity of the rotor toward the journal at the front end of the rotor, and is led out through the gas outlet at the front end of the rotor.

3. The anti-icing air bleed method according to claim 1, characterized in that: The high-temperature and high-pressure gas fills the inner cavity of the rotor and flows forward, and the high-temperature and high-pressure gas is led out through the gas outlet at the front end of the rotor, and the leading-out position is sealed by the grate teeth.

4. The anti-icing air bleed method according to claim 1, characterized in that: The high-temperature and high-pressure gas enters the air cavity inside the guide vane through the air inlet at the lower end of the adjustable guide vane (4), heating the adjustable guide vane (4) to prevent icing.

5. An anti-icing air bleed structure, characterized in that: The structure is applied to the anti-icing and air bleed method described in any one of claims 1 to 4, wherein the anti-icing and air bleed structure includes: a rear end air bleed hole (1) is opened at the drum structure of the rear end blade disk (2) in the rotor inner cavity, a front end air outlet (8) is opened at the front end journal structure of the rotor, and an air inlet is arranged at the lower end of the adjustable guide vane (4).

6. The anti-icing air bleed structure according to claim 5, characterized in that: The blade disk (2) and the rear compressor flow passage are sealed by means of comb teeth.

7. The anti-icing air bleed structure according to claim 5, characterized in that: The leading-out position of the front air outlet (8) is sealed by means of comb teeth.

8. The anti-icing air bleed structure according to claim 5, characterized in that: The joint between the rotor and the stator is sealed with comb teeth.

9. The anti-icing air bleed structure according to claim 8, characterized in that: The rotor comprises: a compressor disc, a grate disc and a tie rod; wherein the compressor disc, the grate disc and the tie rod are fixedly connected; the stator comprises a grate bushing, and the grate bushing and the grate disc are sealed by grate teeth.

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