Inlet air precooling heat exchanger and splitter plate integrated structure and aero-engine

Abstract

The invention relates to the technical field of high-speed engine pre-cooling heat exchangers, in particular to an air inlet pre-cooling heat exchanger and splitter plate integrated structure and an aero-engine, and the air inlet pre-cooling heat exchanger and splitter plate integrated structure comprises a pre-cooling heat exchanger, a splitter plate and a connecting piece; the pre-cooling heat exchanger and the splitter plate are used for being installed in the air inlet channel. A partition piece is formed in the air inlet channel and divides the air inlet channel into a stamping channel and a turbine channel. The precooling heat exchanger and the splitter plate are rotationally connected with the connecting piece; the connecting piece is mounted on the separating piece; the precooling heat exchanger and the splitter plate at least have three working states: in the first working state, the precooling heat exchanger and the splitter plate block the stamping channel; in a second working state, the precooling heat exchanger blocks the turbine channel, and the splitter plate blocks the stamping channel; and in the third working state, the precooling heat exchanger and the splitter plate block the turbine channel. The occupied axial length is shortened, and the structural arrangement of the precooling heat exchanger in the flow channel is facilitated.

Description

Technical Field

[0001] The present disclosure relates to the technical field of high-speed engine precooling heat exchangers, and in particular to an integrated structure of an intake air precooling heat exchanger and a splitter plate and an aero-engine. Background Art

[0002] The high speed of aircraft has extremely important military and civilian value. The mainstream solution is to combine aviation turbine engine with ramjet engine to form a turbine-based combined cycle engine (TBCC). However, there is a gap between the maximum speed of turbine engine that can meet the thrust requirements of aircraft and the minimum speed of ramjet engine, commonly known as the thrust gap, which seriously restricts the development of TBCC technology.

[0003] Aviation turbine engines are the mainstream aviation engine solution because of their horizontal take-off and landing, reusability, and high specific impulse. However, the aerodynamic heating effect usually limits the flight limit of modern advanced aviation turbine engines to Ma2.5. To further increase the flight speed of the turbine, one of the main solutions is to use a heat exchanger structure to cool the intake air. The temperature of the turbine inlet airflow is reduced to offset the increase in intake air temperature caused by the aerodynamic heating effect during high-speed flight, allowing the turbine to fly at a higher speed, thereby achieving relay with the ramjet.

[0004] The following problem still exists in the prior art: the precooling heat exchanger often occupies a relatively long axial length in the flow channel in front of the engine, such as patent document CN115571350B, which brings difficulties to the structural arrangement of the precooling heat exchanger in the flow channel. Summary of the invention

[0005] The present disclosure is proposed in view of the above problems, and provides an integrated structure of an intake air precooling heat exchanger and a splitter plate, and an aircraft engine.

[0006] According to one aspect of the present disclosure, there is provided an integrated structure of an intake air precooling heat exchanger and a splitter plate, which includes a precooling heat exchanger, a splitter plate and a connector;

[0007] The precooling heat exchanger and the splitter plate are used to be installed in the air intake duct; a partition is formed in the air intake duct, and the partition divides the air intake duct into a ram channel and a turbine channel;

[0008] The precooling heat exchanger and the diverter plate are both rotatably connected to the connecting member; the connecting member is mounted on the partition; and a ventilation hole is formed on the precooling heat exchanger;

[0009] The precooling heat exchanger and the diverter plate have at least three working states:

[0010] In the first working state, the precooling heat exchanger and the diverter plate block the stamping channel;

[0011] In the second working state, the precooling heat exchanger blocks the turbine channel, and the diverter plate blocks the ram channel;

[0012] In the third working state, the precooling heat exchanger and the diverter plate block the turbine channel.

[0013] According to an integrated structure of an intake air precooling heat exchanger and a splitter plate according to one aspect of the present disclosure, the connecting member includes a connecting frame, a first rotating shaft, a second rotating shaft and a third rotating shaft;

[0014] The connecting frame is fixedly arranged on the partition, and the first rotating shaft, the second rotating shaft and the third rotating shaft are all rotatably connected to the connecting frame;

[0015] The precooling heat exchanger is fixedly connected to the first rotating shaft, and the diverter plate is fixedly connected to the second rotating shaft; the third rotating shaft is used to be connected to a driver; and the third rotating shaft is used to independently drive the first rotating shaft and the second rotating shaft to rotate.

[0016] According to an integrated structure of an intake air precooling heat exchanger and a splitter plate according to one aspect of the present disclosure, a first gear is mounted on the first rotating shaft, and a second gear is mounted on the second rotating shaft;

[0017] The third rotating shaft is provided with a partial tooth structure along the circumference;

[0018] The partial tooth structure can be intermittently connected to the first gear; the partial tooth structure can be intermittently connected to the second gear; so that when the third shaft rotates in one direction, the precooling heat exchanger and the diverter plate can be switched to the first working state, and when the third shaft rotates in another direction, the precooling heat exchanger and the diverter plate can be switched to the third working state.

[0019] According to an integrated structure of an intake precooling heat exchanger and a diverter plate according to one aspect of the present disclosure, the precooling heat exchanger and the diverter plate can pass through a second working state during a process of switching from a first working state to a third working state, or from a third working state to the first working state.

[0020] According to an aspect of the present disclosure, the air intake precooling heat exchanger and the splitter plate are integrated into a structure, and the precooling heat exchanger and the splitter plate also have a transition state, and the transition state is: the precooling heat exchanger does not completely block the turbine channel or the splitter plate does not completely block the ram channel.

[0021] According to the integrated structure of the intake air precooling heat exchanger and the splitter plate according to one aspect of the present disclosure, when the speed is lower than the first speed, the precooling heat exchanger and the splitter plate are in a first working state.

[0022] According to the integrated structure of the intake air precooling heat exchanger and the splitter plate according to one aspect of the present disclosure, when the speed is not less than the first speed and less than the second speed, the precooling heat exchanger and the splitter plate are in the second working state.

[0023] According to the integrated structure of the intake air precooling heat exchanger and the splitter plate according to one aspect of the present disclosure, when the speed is not less than the second speed, the precooling heat exchanger and the splitter plate are in the third working state.

[0024] According to an integrated structure of an intake air pre-cooling heat exchanger and a splitter plate according to one aspect of the present disclosure, the first speed is between Mach 2.2 and 2.8, and the second speed is between Mach 3.2 and 3.8.

[0025] According to another aspect of the present disclosure, an aircraft engine is also proposed, which includes an integrated structure of an intake air pre-cooling heat exchanger and a splitter plate as described in any one of the above items.

[0026] As will be described in detail below, according to the integrated structure of the intake precooling heat exchanger and the diverter plate and the aircraft engine of the embodiment of the present disclosure, by setting the precooling heat exchanger and the diverter plate as an integrated structure rotatably arranged with the connecting piece, it is possible to switch within the ram channel and the turbine channel. By rotating the precooling heat exchanger and the diverter plate, the precooling heat exchanger and the diverter plate can have at least three working states. While providing multiple working states, the occupied axial length is shortened, thereby facilitating the structural arrangement of the precooling heat exchanger in the flow channel.

[0027] It is to be understood that both the foregoing general description and the following detailed description are exemplary, and are intended to provide further explanation of the technology as claimed. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] The above and other purposes, features and advantages of the present disclosure will become more apparent by describing the embodiments of the present disclosure in more detail in conjunction with the accompanying drawings. The accompanying drawings are used to provide a further understanding of the embodiments of the present disclosure and constitute a part of the specification. Together with the embodiments of the present disclosure, they are used to explain the present disclosure and do not constitute a limitation of the present disclosure. In the accompanying drawings, the same reference numerals generally represent the same components or steps.

[0029] Figure 1 is a structural schematic diagram of the integrated structure of the air intake precooling heat exchanger and the splitter plate proposed in the present disclosure in the first working state;

[0030] Figure 2 yes Figure 1 A partial enlarged schematic diagram of

[0031] Figure 3 is a structural schematic diagram of the integrated structure of the air intake precooling heat exchanger and the splitter plate proposed in the present disclosure in the second working state;

[0032] Figure 4 yes Figure 3 A partial enlarged schematic diagram of

[0033] Figure 5 is a structural schematic diagram of the integrated structure of the air intake precooling heat exchanger and the splitter plate proposed in the present disclosure in a third working state;

[0034] Figure 6 yes Figure 5 A partial enlarged schematic diagram of

[0035] Figure 7 is a three-dimensional diagram of the integrated structure of the intake air precooling heat exchanger and the splitter plate proposed in the present disclosure;

[0036] Figure 8 yes Figure 7 A partial enlarged schematic diagram of .

[0037] Description of reference numerals:

[0038] 1-precooling heat exchanger, 2-dividing plate, 3-connecting piece, 4-inlet duct;

[0039] 31-connecting frame, 32-first rotating shaft, 33-second rotating shaft, 34-third rotating shaft, 35-first gear; 36-second gear, 37-partial gear structure;

[0040] 41 - separator, 42 - ram channel, 43 - turbine channel. DETAILED DESCRIPTION

[0041] In order to make the purpose, technical solution and advantages of the present disclosure more obvious, the exemplary embodiments according to the present disclosure will be described in detail with reference to the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present disclosure, rather than all the embodiments of the present disclosure, and it should be understood that the present disclosure is not limited to the exemplary embodiments described here.

[0042] In view of the problems raised in the background technology, the present disclosure can solve the problem by making the heat exchanger and the diverter plate into an integrated structure. By combining the thin layer precooling heat exchanger and the diverter plate, smooth switching of the three main working states and the transition state is achieved, and the axial size occupied by the precooling heat exchanger is saved.

[0043] For details, please refer to Figures 1 to 8The present disclosure proposes an integrated structure of an intake precooling heat exchanger and a diverter plate, which includes a precooling heat exchanger 1, a diverter plate 2 and a connector 3; the connector 3 is used to connect the precooling heat exchanger 1 and the diverter plate 2 and provide support.

[0044] Specifically, the precooling heat exchanger 1 and the splitter plate 2 are used to be installed in the air intake duct 4; a partition 41 is formed in the air intake duct 4, and the partition 41 divides the air intake duct 4 into a ram channel 42 and a turbine channel 43. In a specific implementation, the partition 41 can be a wall of the turbine channel 43.

[0045] The precooling heat exchanger 1 is used to cool the air entering the turbine channel 43. The splitter plate 2 is used to split the gas entering the ram channel 42 and the gas entering the turbine channel 43 to achieve air distribution.

[0046] Specifically, the precooling heat exchanger 1 and the diverter plate 2 are both rotatably connected to the connecting member 3; the connecting member 3 is installed on the partition 41; ventilation holes are formed on the precooling heat exchanger 1; that is, air can pass through the precooling heat exchanger 1, but cannot pass through the diverter plate.

[0047] The precooling heat exchanger 1 and the diverter plate 2 have at least three working states:

[0048] Please refer to Figure 1 and Figure 2 In the first working state, the precooling heat exchanger 1 and the splitter plate 2 block the ramjet channel 42; when the speed is lower than the first speed, the precooling heat exchanger 1 and the splitter plate 2 are in the first working state. That is, when the speed of the aircraft is lower than the first speed, it is in a low mode, air enters from the turbine channel, the turbine engine works, and the ramjet engine does not work. In a specific implementation, the first speed is between 2.2 and 2.8 Mach, preferably 2.5 Mach.

[0049] Please refer to Figure 3 and Figure 4 In the second working state, the precooling heat exchanger 1 blocks the turbine channel 43, and the splitter plate 2 blocks the ramjet channel 42. When the speed is not less than the first speed and less than the second speed, the precooling heat exchanger 1 and the splitter plate 2 are in the second working state. At this time, it is a medium-speed mode, air enters from the turbine channel, passes through the precooling heat exchanger 1 and enters the turbine engine, the turbine engine works, and the ramjet engine does not work. In the specific implementation, the second speed is between 3.2 and 3.8 Mach, wherein 3.5 Mach is preferred.

[0050] Please refer to Figure 5 and Figure 6In the third working state, the precooling heat exchanger 1 and the splitter plate 2 block the turbine channel 43. When the speed is not less than the second speed, the precooling heat exchanger 1 and the splitter plate 2 are in the third working state. At this time, it is in the high-speed mode, air enters from the ramjet channel, the ramjet engine works, and the turbine engine does not work. Preferably, the precooling heat exchanger 1 can be a thin-layer precooler.

[0051] This arrangement can save axial size and facilitate arrangement on an aircraft engine.

[0052] The use of an integrated structure of the precooling heat exchanger and the manifold has brought up another problem. The precooling heat exchanger and the manifold need to be rotated to different positions according to the engine speed, and they need to have bidirectional rotation capabilities, which requires accurate judgment and control of their rotation positions. At the same time, to avoid collisions between the manifold and the precooling heat exchanger and damage to the heat exchange structure, their respective positions must also be accurately controlled. Finally, the switching of the three modes is not achieved overnight, but a continuous and smooth process, that is, the engine mode conversion process, and their respective positions must also be accurately controlled.

[0053] Traditional cable-type devices can produce motion effects, but it is difficult to achieve bidirectional rotation and it is not easy to accurately control the rotation position. If a complex position feedback and control mechanism is used, the system complexity will be too large.

[0054] To do this, please refer to Figure 7 and Figure 8 In the present disclosure, the connecting member 3 includes a connecting frame 31, a first rotating shaft 32, a second rotating shaft 33 and a third rotating shaft 34. Specifically, the connecting frame 31 is fixedly arranged on the partition 41, and the first rotating shaft 32, the second rotating shaft 33 and the third rotating shaft 34 are all rotatably connected to the connecting frame 31; the precooling heat exchanger 1 is fixedly connected to the first rotating shaft 32, and the diverter plate 2 is fixedly connected to the second rotating shaft 33; the third rotating shaft 34 is used to connect to a driver; the third rotating shaft 34 is used to drive the first rotating shaft 32 and the second rotating shaft 33 to rotate independently.

[0055] In a specific implementation, a first gear 35 is installed on the first rotating shaft 32, and a second gear 36 is installed on the second rotating shaft 33. The third rotating shaft 34 is provided with a partial tooth structure 37 along the circumference; in a specific implementation, the partial tooth structure 37 is a plurality of tooth structures distributed in a fan shape along the third rotating shaft 34. When the third rotating shaft 34 rotates in the same direction, the partial tooth structure 37 is meshed with the first gear 35 and the second gear 36 respectively. That is, the partial tooth structure 37 is not meshed with the first gear 35 and the second gear 36 at the same time.

[0056] The partial tooth structure 37 can be intermittently connected to the first gear 35; the partial tooth structure 37 can be intermittently connected to the second gear 36; so that when the third shaft 34 rotates in one direction, the precooling heat exchanger 1 and the diverter plate 2 can be switched to the first working state, and when the third shaft 34 rotates in another direction, the precooling heat exchanger 1 and the diverter plate 2 can be switched to the third working state.

[0057] In a specific implementation, the precooling heat exchanger 1 and the diverter plate 2 can pass through the second working state during the process of switching from the first working state to the third working state, or during the process of switching from the third working state to the first working state.

[0058] In the specific implementation, take the aircraft acceleration state as an example:

[0059] The precooling heat exchanger 1 and the diverter plate 2 are in the first working state, and the precooling heat exchanger 1 and the diverter plate 2 block the stamping channel 42. At this time, at the entrance of the stamping channel, along the entrance direction of the stamping channel, the precooling heat exchanger 1 and the diverter plate 2 are blocked in sequence. When acceleration is required, the third shaft 34 is driven along the first direction, and the partial tooth structure 37 on the third shaft 34 first engages with the first gear 35, and the precooling heat exchanger 1 is driven to the position of blocking the turbine channel 43. During this process, the diverter plate 2 does not rotate, and switches from the first working state to the second working state. During the whole process, the ramjet engine does not work, and the turbine engine works.

[0060] The third rotating shaft 34 is driven to rotate in the first direction, and the partial tooth structure 37 is no longer meshed with the first gear 35, but begins to mesh with the second gear 36. As the third rotating shaft 34 continues to rotate, the second gear 36 meshes and begins to rotate until the splitter plate 2 is rotated to block the inlet of the turbine channel 43. At this time, the third working state is entered. Along the inlet direction of the turbine channel 43, the splitter plate 2 and the precooling heat exchanger 1 are covered in sequence.

[0061] In a specific implementation, when the aircraft decelerates: the third rotating shaft 34 is rotated in the second direction, and the above process switches from the third working state to the second working state and then to the first working state. In a specific implementation process, the partial tooth structure 37 first meshes with the second gear 36 and then meshes with the first gear 35. The first direction is clockwise or counterclockwise, and the second direction is opposite to the first direction.

[0062] In a specific implementation, the precooling heat exchanger 1 and the splitter plate 2 also have a transition state, and the transition state is: the precooling heat exchanger 1 does not completely block the turbine channel 43 or the splitter plate 2 does not completely block the ramming channel 42.

[0063] There are two transition states, namely, one is that the precooling heat exchanger 1 partially blocks the turbine channel 43 during the meshing of the partial tooth structure 37 with the first gear 35, and the other is that the splitter plate 2 partially blocks the stamping channel during the meshing of the partial tooth structure 37 with the second gear 36.

[0064] According to another aspect of the present invention, an aircraft engine is also proposed, which includes the integrated structure of the intake pre-cooling heat exchanger and the splitter plate as described in any one of the present disclosures.

[0065] The above describes the integrated structure of the intake precooling heat exchanger and the diverter plate and the aircraft engine according to the embodiment of the present disclosure with reference to the accompanying drawings. According to the integrated structure of the intake precooling heat exchanger and the diverter plate and the aircraft engine according to the embodiment of the present disclosure, by setting the precooling heat exchanger and the diverter plate as an integrated structure rotatably arranged with the connecting piece, it is possible to switch within the ram channel and the turbine channel. By rotating the precooling heat exchanger and the diverter plate, the precooling heat exchanger and the diverter plate can have at least three working states. While providing multiple working states, the occupied axial length is shortened, thereby facilitating the structural arrangement of the precooling heat exchanger in the flow channel.

[0066] The basic principles of the present disclosure are described above in conjunction with specific embodiments. However, it should be noted that the advantages, strengths, effects, etc. mentioned in the present disclosure are only examples and not limitations, and it cannot be considered that these advantages, strengths, effects, etc. are required by each embodiment of the present disclosure. In addition, the specific details disclosed above are only for the purpose of illustration and ease of understanding, and are not limitations. The above details do not limit the present disclosure to the necessity of adopting the above specific details to be implemented.

[0067] The block diagrams of the devices, apparatuses, equipment, and systems involved in this disclosure are only illustrative examples and are not intended to require or imply that they must be connected, arranged, and configured in the manner shown in the block diagrams. As will be appreciated by those skilled in the art, these devices, apparatuses, equipment, and systems can be connected, arranged, and configured in any manner. Words such as "including," "comprising," "having," and the like are open words, referring to "including but not limited to," and can be used interchangeably therewith. The words "or" and "and" used herein refer to the words "and / or," and can be used interchangeably therewith, unless the context clearly indicates otherwise. The word "such as" used herein refers to the phrase "such as but not limited to," and can be used interchangeably therewith.

[0068] Additionally, as used herein, "or" used in a list of items beginning with "at least one" indicates a separate list, so that, for example, a list of "at least one of A, B, or C" means A or B or C, or AB or AC or BC, or ABC (i.e., A and B and C). Furthermore, the word "exemplary" does not mean that the example described is preferred or better than other examples.

[0069] It should also be noted that in the system and method of the present disclosure, each component or each step can be decomposed and / or recombined. Such decomposition and / or recombination should be regarded as equivalent solutions of the present disclosure.

[0070] Various changes, substitutions, and modifications of the techniques described herein may be made without departing from the teachings defined by the appended claims. Furthermore, the scope of the claims of the present disclosure is not limited to the specific aspects of the processes, machines, manufactures, compositions of events, means, methods, and actions described above. Currently existing or later to be developed processes, machines, manufactures, compositions of events, means, methods, or actions that perform substantially the same functions or achieve substantially the same results as the corresponding aspects described herein may be utilized. Thus, the appended claims include such processes, machines, manufactures, compositions of events, means, methods, or actions within their scope.

[0071] The above description of the disclosed aspects is provided to enable any person skilled in the art to make or use the present disclosure. Various modifications to these aspects will be readily apparent to those skilled in the art, and the general principles defined herein may be applied to other aspects without departing from the scope of the present disclosure. Therefore, the present disclosure is not intended to be limited to the aspects shown herein, but rather to the widest scope consistent with the principles and novel features disclosed herein.

[0072] The above description has been given for the purpose of illustration and description. In addition, this description is not intended to limit the embodiments of the present disclosure to the forms disclosed herein. Although multiple example aspects and embodiments have been discussed above, those skilled in the art will recognize certain variations, modifications, changes, additions and sub-combinations thereof.

Claims

1. An integrated structure of an air intake precooling heat exchanger and a splitter plate, characterized in that: It comprises a precooling heat exchanger (1), a diverter plate (2) and a connecting piece (3); The precooling heat exchanger (1) and the splitter plate (2) are used to be installed in an air intake duct (4); a partition (41) is formed in the air intake duct (4), and the partition (41) divides the air intake duct (4) into a ram channel (42) and a turbine channel (43); The precooling heat exchanger (1) and the diverter plate (2) are both rotatably connected to the connecting member (3); the connecting member (3) is mounted on the partition (41); and ventilation holes are formed on the precooling heat exchanger (1); The precooling heat exchanger (1) and the diverter plate (2) have at least three working states: In a first working state, the precooling heat exchanger (1) and the diverter plate (2) block the stamping channel (42); In the second working state, the precooling heat exchanger (1) blocks the turbine channel (43), and the diverter plate (2) blocks the ram channel (42); In the third working state, the precooling heat exchanger (1) and the diverter plate (2) block the turbine channel (43).

2. The integrated structure of the air intake precooling heat exchanger and the manifold according to claim 1, characterized in that: The connecting member (3) comprises a connecting frame (31), a first rotating shaft (32), a second rotating shaft (33) and a third rotating shaft (34); The connecting frame (31) is fixedly arranged on the partition (41), and the first rotating shaft (32), the second rotating shaft (33) and the third rotating shaft (34) are all rotatably connected to the connecting frame (31); The precooling heat exchanger (1) is fixedly connected to the first rotating shaft (32), and the diverter plate (2) is fixedly connected to the second rotating shaft (33); the third rotating shaft (34) is used to be connected to a driver; the third rotating shaft (34) is used to independently drive the first rotating shaft (32) and the second rotating shaft (33) to rotate.

3. The integrated structure of the air intake precooling heat exchanger and the manifold according to claim 2, characterized in that: A first gear (35) is mounted on the first rotating shaft (32), and a second gear (36) is mounted on the second rotating shaft (33); The third rotating shaft (34) is provided with a partial tooth structure (37) along the circumferential direction; The partial tooth structure (37) can be intermittently connected to the first gear (35); the partial tooth structure (37) can be intermittently connected to the second gear (36); so that when the third rotating shaft (34) rotates in one direction, the precooling heat exchanger (1) and the diverter plate (2) can be switched to the first working state, and when the third rotating shaft (34) rotates in the other direction, the precooling heat exchanger (1) and the diverter plate (2) can be switched to the third working state.

4. The integrated structure of the air intake precooling heat exchanger and the manifold according to claim 3, characterized in that: During the process of the precooling heat exchanger (1) and the diverter plate (2) switching from the first working state to the third working state, or switching from the third working state to the first working state, the second working state can be passed.

5. The integrated structure of the air intake precooling heat exchanger and the manifold according to any one of claims 1 to 4, characterized in that: The precooling heat exchanger (1) and the diverter plate (2) also have a transition state, wherein the transition state is: the precooling heat exchanger (1) does not completely block the turbine channel (43) or the diverter plate (2) does not completely block the ramming channel (42).

6. The integrated structure of the air intake precooling heat exchanger and the manifold according to any one of claims 1 to 4, characterized in that: When the speed is lower than the first speed, the precooling heat exchanger (1) and the diverter plate (2) are in a first working state.

7. The integrated structure of the air intake precooling heat exchanger and the manifold according to claim 6, characterized in that: When the speed is not less than the first speed and less than the second speed, the precooling heat exchanger (1) and the diverter plate (2) are in a second working state.

8. The integrated structure of the air intake precooling heat exchanger and the manifold according to claim 6, characterized in that: When the speed is not less than the second speed, the precooling heat exchanger (1) and the diverter plate (2) are in a third working state.

9. The integrated structure of the air intake precooling heat exchanger and the manifold according to claim 8, characterized in that: The first speed is between Mach 2.2 and 2.8, and the second speed is between Mach 3.2 and 3.

8.

10. An aircraft engine, characterized in that: It comprises an integrated structure of an intake air precooling heat exchanger and a splitter plate as described in any one of claims 1 to 9.

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