Blade cooling air entraining structure and method, engine, turbine and stator blade

Abstract

The invention relates to a blade cooling air entraining structure, an air entraining method, an engine, a turbine and a stator blade, and an air entraining chamber is formed by a radial space between a casing and the root of the stator blade; the cooling air entraining structure comprises an inlet part arranged at the root part of the stator blade, and a cooling air entraining part arranged at the root part of the stator blade, wherein the inlet part can receive the cooling air and output the cooling air to a cooling air film hole of the stator blade; and the confluence assembly comprises a separator and a communicating piece, the separator separates the inlet part and the air guide hole, a confluence cavity is formed by a radial space between the separator and the air guide hole of the cartridge receiver, and airflow in the confluence cavity is conveyed to the inlet part through the communicating piece.

Description

Technical Field

[0001] The invention relates to a blade cooling air entrainment structure, an air entrainment method, an engine, a turbine and a stator blade. Background Art

[0002] Gas turbine engines, such as aircraft engines, have high-temperature working environments in their high-pressure turbines. As the temperature before the turbine continues to rise, higher requirements are placed on the cooling of the high-pressure turbine blades, especially the first-stage guide vanes of the high-pressure turbine. High-pressure turbine blades can use hollow internal cooling blades. The cold air used is introduced from the compressor end into the high-pressure turbine casing assembly through the cooling pipeline, and then enters the blade internal cooling channel through the pressure equalizing orifice plate. The cold air leakage along the way and the cold air flow efficiency will directly affect the cooling capacity of the blades, thereby affecting the cooling effect of the blades, and are prone to blade failures such as ablation.

[0003] In an existing solution, the pressure equalizing orifice plate and the stator components at the front and rear ends of the blades are tightly sealed, resulting in low flow efficiency of the cold air.

[0004] The present invention designs a blade air bleed pipeline sealing structure, which effectively reduces the cold air leakage along the blade air bleed, ensures the sealing performance, has high air bleed efficiency, and is simple and feasible to assemble. Summary of the invention

[0005] An object of the present invention is to provide a blade cooling air bleed structure.

[0006] An object of the present invention is to provide a blade cooling air bleed method.

[0007] An object of the present invention is to provide a gas turbine engine.

[0008] An object of the present invention is to provide a turbine.

[0009] An object of the present invention is to provide a stator blade.

[0010] According to one aspect of the present invention, a blade cooling air bleed structure comprises an air bleed chamber formed by the radial space between the casing and the root of the stator blade; the blade cooling air bleed structure comprises: an inlet portion arranged at the root of the stator blade, the inlet portion being capable of receiving the cooling air and outputting it to the cooling air film hole of the stator blade; a confluence component comprising an isolating member and a connecting member, the isolating member separating the inlet portion from the air bleed hole, the radial space between the isolating member and the air bleed hole of the casing forming a confluence chamber, the airflow in the confluence chamber being transported to the cooling air film hole through the connecting member inlet portion; wherein, the connecting piece includes a connecting piece body and an extension portion extending radially outward from the connecting piece body, the upstream end of the connecting piece body is located in the confluence chamber, and the connecting piece body axially penetrates the through hole provided by the isolation piece, so that the downstream end of the connecting piece body is connected to the inlet portion; the isolation piece also includes a receiving groove, the receiving groove is arranged corresponding to the extension portion, and there is a gap between the axial space formed by the receiving groove walls at the axial ends of the receiving groove and the axial dimension of the extension portion, so that the extension portion and the receiving groove have an axial displacement space.

[0011] In one or more embodiments of the bleed air structure, the inlet portion includes a tubular member extending from the root of the stator blade to the bleed air chamber, and the tubular member and the downstream end of the connecting member body are sleeved and connected to each other.

[0012] In one or more embodiments of the air entrainment structure, the connection structure in which one of the tubular member and the downstream end of the connecting member body is sleeved with the other comprises a conical connection structure.

[0013] In one or more embodiments of the air entraining structure, the connection structure between the tubular member and the downstream end of the connecting member body has a first sealing member.

[0014] In one or more embodiments of the air ducting structure, the isolation member includes a pressure equalizing plate and a cover plate which are separately arranged, and the cover plate is stacked on the pressure equalizing plate. The pressure equalizing plate and the cover plate both have a through hole portion (,) to provide the through hole, and at least one of the pressure equalizing plate and the cover plate has an annular groove to provide the accommodating groove.

[0015] In one or more embodiments of the air entraining structure, the cover plate is stacked on the pressure equalizing plate via a threaded connection structure.

[0016] In one or more embodiments of the air entraining structure, at least one of the extending portion and the accommodating groove walls at both axial ends of the accommodating groove is provided with a second sealing member.

[0017] According to one aspect of the present invention, an air bleed method adopts the air bleed structure as described above, and the air bleed method includes: cooling air is introduced into the air bleed chamber from the air bleed holes of the casing, gathered to the upstream end of the connecting piece body inside the air bleed chamber, and transported to the inlet of the stator blade connected to the downstream end of the connecting piece body through the connecting piece body.

[0018] A turbine according to one aspect of the present invention comprises the bleed air structure as described in the above embodiments.

[0019] In one or more embodiments of the turbine, the stator blades comprise first stage guide blades of a high pressure turbine.

[0020] A gas turbine engine according to one aspect of the present invention comprises the bleed air structure as described in the above embodiments.

[0021] A stator blade according to one aspect of the present invention is used in the air bleed structure as described in the above embodiment, wherein the inlet portion is provided at the root of the stator blade, and the inlet portion comprises a tubular member extending outward from the root of the stator blade.

[0022] The improved effects of the present invention include but are not limited to: through the arrangement of the confluence assembly, the cooling airflow is gathered in the confluence chamber and then flows directly into the inlet of the stator blade through the connecting piece, so that the flow efficiency of the cooling airflow is high, and through the arrangement of the extension part and the accommodating groove, the airflow leakage is further reduced, and the arrangement of the axial displacement space absorbs the installation error of the position concentricity of the through hole of the isolation piece and the inlet, so that the assembly process is simple. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] 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. It should be noted that the drawings are only examples and are not drawn to scale, and should not be used as a limitation on the actual scope of protection required by the present invention, wherein:

[0024] Figure 1 It is a schematic diagram of the local structure of a turbine where a cooling air bleed structure is located according to an embodiment.

[0025] Figure 2 FIG. 1 is a schematic diagram of a cooling air entrainment structure according to an embodiment of the present invention.

[0026] Figure 3 It is a schematic structural diagram of a connecting piece of a cooling air bleed structure according to an embodiment.

[0027] Figure 4 The figure is a schematic structural diagram of a cover plate of a cooling air entraining structure according to an embodiment.

[0028] Some reference numerals:

[0029] 10-Cooling air bleed structure

[0030] 100-Receiver

[0031] 101-Air vent

[0032] 200-Stator blades

[0033] 201-Entrance Department

[0034] 2010-Tube

[0035] 2011-Conical connection structure

[0036] 300-Air bleed chamber

[0037] 301-Confluence chamber

[0038] 1-Confluence components

[0039] 11-Isolator

[0040] 111-Through hole

[0041] 112-Accommodation slot

[0042] 1121, 1122-accommodating groove wall

[0043] 1120-Axial displacement space

[0044] 113-Equalizing plate

[0045] 114-Cover

[0046] 1131, 1141-Through hole part

[0047] 115-Ring groove

[0048] 116-Threaded connection structure

[0049] 1160-bolt structure

[0050] 12-Connecting parts

[0051] 121-Connecting piece body

[0052] 1211- Upstream end of the connecting piece body

[0053] 1212- Downstream end of the connecting piece body

[0054] 122-Extension

[0055] 131-First seal

[0056] 132 - Second seal. DETAILED DESCRIPTION

[0057] The following discloses various different implementation methods or embodiments of the subject technical solution. To simplify the disclosure, specific examples of various elements and arrangements are described below. Of course, these are only examples and are not intended to limit the scope of protection of the present invention.

[0058] In addition, the use of "one embodiment", "an embodiment", and / or "some embodiments" means a certain feature, structure or characteristic related to at least one embodiment of the present application. Therefore, it should be emphasized and noted that "one embodiment" or "one embodiment" or "one or more embodiments" mentioned twice or more in different places in this specification do not necessarily refer to the same embodiment. In addition, certain features, structures or characteristics in one or more embodiments of the present application can be appropriately combined.

[0059] The air bleed structure described in the following embodiments is applied to a gas turbine engine, specifically, the first-stage guide blades of a high-pressure turbine of a turbofan engine, where the temperature is relatively high, and therefore the cooling requirements are relatively high. However, this is not limited to this, and for example, it can also be a marine gas turbine engine, a ground gas turbine, etc. As long as it is a stator blade structure with a cooling flow channel, the cooling air bleed structure described in this case can be applied.

[0060] like Figure 1 as well as Figure 2 As shown, in some embodiments, the radial space between the casing 100 and the root of the stator blade 200 constitutes an air bleed chamber 300. Cooling air flows into the air bleed chamber 300 from the air bleed hole 101 of the casing 100. The blade cooling air bleed structure 10 is used to pass the cooling air in the air bleed chamber 300 into the stator blade 200.

[0061] The blade cooling air bleed structure 10 includes an inlet portion 201 provided at the root of the stator blade 200 , and the inlet portion 201 can receive cooling air and output the cooling air to the cooling air film holes of the stator blade 200 .

[0062] The air bleed structure 10 also includes a confluence assembly 1, including an isolating member 11 and a connecting member 12. The isolating member 11 separates the inlet portion 201 from the air bleed hole 101. The radial space between the isolating member 11 and the air bleed hole 101 of the casing 100 forms a confluence chamber 301. The airflow in the confluence chamber 301 is transported to the inlet portion 201 through the connecting member 12.

[0063] The connecting piece 12 includes a connecting piece body 121 and an extension portion 122 extending radially outward from the connecting piece body 12, the upstream end 1211 of the connecting piece body 121 is located in the confluence chamber 301, and the connecting piece body 121 axially penetrates the through hole 111 provided by the isolation piece 11, so that the downstream end 1212 of the connecting piece body 121 is connected to the inlet portion 201; the isolation piece 11 also includes a receiving groove 112, and the receiving groove 112 is arranged corresponding to the extension portion 122. There is a gap between the axial space formed by the receiving groove walls 1121, 1122 at the axial ends of the receiving groove 112 and the axial dimension of the extension portion 122, so that the extension portion 122 and the receiving groove 112 have an axial displacement space 1120.

[0064] Preferably, in some embodiments, at least one of the accommodating groove walls 1121 , 1122 at both axial ends of the extension portion 122 and the accommodating groove 112 is provided with a second seal 132 , such as a sealing ring, to further improve the sealing performance of the air bleed structure and optimize the anti-leakage effect of the airflow.

[0065] The “axial direction” and “radial direction” in the above embodiments refer to the axial direction and radial direction of the connecting piece 12 itself, rather than the axial direction and radial direction of the engine.

[0066] The meaning of "stator blades" above is similar to the general meaning in this field, that is, the important structure of the impeller machinery, including rotor blades and stator blades, which do work on the airflow through the rotor blades and adjust the airflow direction through the stator blades to produce airflow conditions suitable for the rotor blades. For example, for a turbine, such as a high-pressure turbine, the high-temperature combustion gas generated from the combustion chamber needs to be guided by the first-stage guide blades. This is the position where the temperature of the gas turbine engine is higher, so a better cooling effect is required.

[0067] The beneficial effects of adopting the above-described embodiments include but are not limited to: through the arrangement of the confluence assembly, the cooling airflow is gathered in the confluence chamber and then flows directly into the inlet of the stator blade through the connecting piece, so that the flow efficiency of the cooling airflow is high, and through the arrangement of the extension portion and the accommodating groove, the airflow leakage is further reduced, and the arrangement of the axial displacement space absorbs the installation error of the position concentricity of the through hole of the isolation piece and the inlet portion, so that the assembly process is simple.

[0068] Continue to refer Figure 1 as well as Figure 2 As shown, preferably, in some embodiments, the structure of the inlet portion 201 may include a tubular member 2010 extending from the root of the stator blade 200 to the bleed air chamber 300, and the tubular member 2010 and the downstream end 1212 of the connecting member body 121 are sleeved and connected to each other. Figure 2As shown, the tubular member 2010 is located at the downstream end 1212 of the connecting member body 121 which is radially sleeved on the periphery, and the inner wall of the tubular member 2010 is connected to the outer wall of the connecting member body 121 .

[0069] Continue to refer Figure 2 As shown, the connection structure between the tubular member 2010 and the downstream end 1212 of the connecting member body 121 can be that the connection structure of one side and the other side mutually sleeved includes a conical surface connection structure 2011. The conical surface connection has a good sealing effect and can further prevent cooling gas leakage. Preferably, the connection structure between the tubular member 2010 and the downstream end 1212 of the connecting member body 121 has a first sealing member 131, thereby further improving the sealing effect.

[0070] refer to Figure 2 , Figure 3 as well as Figure 4 As shown, in some embodiments, the specific structure of the isolation member 11 can be a structure of split component assembly. For example, the isolation member 11 includes a pressure equalizing plate 113 and a cover plate 114 which are separately arranged, and the cover plate 114 is stacked on the pressure equalizing plate 113. The pressure equalizing plate 113 and the cover plate 114 both have through-hole portions 1131 and 1141 to provide the through-hole 111, and at least one of the pressure equalizing plate 113 and the cover plate 114 has an annular groove 115 to provide a receiving groove 112. For example, as shown in the figure, the cover plate 114 has an annular groove 115, and the pressure equalizing plate 113 is a substantially planar structure at the corresponding position, and the receiving groove 112 is formed by the annular groove 115 and the pressure equalizing plate 113 of the planar structure. The structure of the pressure equalizing plate, the cover plate and the annular groove makes it easy to carry out the installation process of the connecting member 12 on the isolation member 11.

[0071] It can be understood that the structure of the isolation member 11 is not limited to the split structure described above, and may also be an integrated structure, for example, the pressure equalizing plate 113 and the cover plate 114 are integrally formed by additive manufacturing.

[0072] like Figure 2 As shown, in some embodiments, the cover plate 114 is stacked on the pressure equalizing plate 113 through a threaded connection structure 116, for example, Figure 2 The bolt structure 1160 is shown as a stacking connection. However, this is not a limitation, and for example, the connection can also be made by a threaded connection structure such as a screw. The beneficial effect of using a threaded connection structure is that the cost is low and it is easy to implement.

[0073] As introduced above, the present case also provides an air bleed method for blade cooling air, which adopts the cooling air bleed structure 10 introduced in the above embodiment. The air bleed method includes: cooling air is introduced into the bleed chamber 300 from the bleed hole 101 of the casing 100, gathered to the upstream end 1211 of the connecting piece body 121 inside the bleed chamber 300, and transported to the inlet portion 201 of the stator blade 200 connected to the downstream end 1212 of the connecting piece body 121 through the connecting piece body 121.

[0074] In summary, the beneficial effects of the blade cooling air bleed structure, bleed method, engine, turbine, and stator blade introduced in the above embodiments include but are not limited to: through the setting of the confluence component, the cooling air flow is gathered in the confluence chamber and then flows directly into the inlet of the stator blade through the connecting piece, so that the flow efficiency of the cooling air flow is high, and the setting of the extension part and the accommodating groove further reduces the air flow leakage, and the setting of the axial displacement space absorbs the installation error of the position concentricity of the through hole of the isolation part and the inlet part, so that the assembly process is simple.

[0075] Although the present invention is disclosed as above with the above embodiments, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications without departing from the spirit and scope of the present invention. Therefore, any modification, equivalent change and modification made to the above embodiments according to the technical essence of the present invention without departing from the content of the technical solution of the present invention shall fall within the protection scope defined by the claims of the present invention.

Claims

1. A blade cooling air bleed structure (10), wherein the radial space between the casing (100) and the root of the stator blade (200) forms an air bleed chamber (300); characterized in that: The blade cooling air bleed structure (10) comprises: An inlet portion (201) is arranged at the root of the stator blade (200), and the inlet portion (201) is capable of receiving the cooling air and outputting it to the cooling air film hole of the stator blade (200); A confluence assembly (1) comprises an isolating member (11) and a connecting member (12), wherein the isolating member (11) separates the inlet portion (201) from the air inlet hole (101), and a confluence chamber (301) is formed by a radial space between the isolating member (11) and the air inlet hole (101) of the casing (100), and the airflow in the confluence chamber (301) is transported to the inlet portion (201) through the connecting member (12); The connecting piece (12) comprises a connecting piece body (121) and an extension portion (122) extending radially outward from the connecting piece body (12); the upstream end (1211) of the connecting piece body (121) is located in the confluence chamber (301); the connecting piece body (121) axially penetrates the through hole (111) provided by the isolation piece (11), so that the downstream end (1212) of the connecting piece body (121) is connected to the inlet portion (201); the isolation piece (11) further comprises a receiving groove (112), the receiving groove (112) is arranged corresponding to the extension portion (122), and there is a gap between the axial space formed by the receiving groove walls (1121, 1122) at the axial ends of the receiving groove (112) and the axial dimension of the extension portion (122), so that the extension portion (122) and the receiving groove (112) have an axial displacement space (1120).

2. The cooling air entrainment structure (10) according to claim 1, characterized in that: The inlet portion (201) includes a tubular member (2010) extending from the root of the stator blade (200) toward the air induction chamber (300), and the tubular member (2010) and the downstream end (1212) of the connecting member body (121) are sleeved and connected to each other.

3. The cooling air entrainment structure (10) according to claim 2, characterized in that: The connection structure between the tubular member (2010) and the downstream end (1212) of the connecting member body (121), in which one side is sleeved with the other side, comprises a conical surface connection structure (2011).

4. The cooling air entrainment structure (10) according to claim 2, characterized in that: The connection structure between the tubular member (2010) and the downstream end (1212) of the connecting member body (121) comprises a first sealing member (131).

5. The cooling air entrainment structure (10) according to claim 1, characterized in that: The isolation member (11) comprises a pressure equalizing plate (113) and a cover plate (114) which are separately arranged, and the cover plate (114) is stacked on the pressure equalizing plate (113). Both the pressure equalizing plate (113) and the cover plate (114) have through-hole portions (1131, 1141) to provide the through-hole (111), and at least one of the pressure equalizing plate (113) and the cover plate (114) has an annular groove (115) to provide the accommodating groove (112).

6. The cooling air entrainment structure (10) according to claim 5, characterized in that: The cover plate (114) is stacked on the pressure equalizing plate (113) via a threaded connection structure (116).

7. The cooling air entrainment structure (10) according to claim 1, characterized in that: At least one of the accommodating groove walls (1121, 1122) at both axial ends of the extension portion (122) and the accommodating groove (112) is provided with a second sealing member (132).

8. A turbine, characterized in that: It comprises a cooling air bleed structure (10) as claimed in any one of claims 1 to 7.

9. The turbine according to claim 8, characterized in that The stator blades (200) include first-stage guide blades of a high-pressure turbine.

10. A gas turbine engine, characterized in that: It comprises a cooling air bleed structure (10) as claimed in any one of claims 1 to 7.

11. A stator blade (200), characterized in that: For the cooling air bleed structure (10) as claimed in any one of claims 1 to 7, the inlet portion (201) is provided at the root of the stator blade (200), and the inlet portion (201) includes a tubular member (2010) extending from the root of the stator blade (200) to the outside.

12. A method for entraining cooling air for blades, characterized in that: Using the cooling air entrainment structure (10) according to any one of claims 1 to 7, the entrainment method comprises: Cooling air is introduced into the air bleed chamber (300) from the air bleed hole (101) of the casing (100), gathered inside the air bleed chamber (300) to the upstream end (1211) of the connecting piece body (121), and transported through the connecting piece body (121) to the inlet portion (201) of the stator blade (200) connected to the downstream end (1212) of the connecting piece body (121).

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