Guide unit for air flow at inlet of combustion chamber of gas turbine engine

FIELD: engines and pumps.

SUBSTANCE: straightening unit includes two coaxial shells between which the blades passing mainly in radial direction are arranged. Diffuser includes two coaxial walls representing rotation bodies and connected to each other by means of radial partitions. One of the shells of straightening unit is made in the form of single part with one wall of diffuser, which represents rotation body. The other shell of straightening unit is connected to and fixed on the other diffuser wall representing rotation body. Blades of strengthening unit are rigidly connected through one end to one shell of straightening unit and are located at some distance with a small gap from the other shell on the other end.

EFFECT: simpler manufacturing technology of the straightening unit.

15 cl, 8 dwg

The present invention relates to a guiding device for the flow of inlet air into the combustion chamber of a gas turbine engine, such as an aircraft turbojet or turboprop engine.

A device of this type is installed at the outlet of the compressor and includes a rectifying device, behind which is located the diffuser, and the diffuser comprises two coaxial walls, which are the body of rotation and connected to each other by means of radial partitions, and a rectifying device contains two coaxial shells, which are located on the same line in the axial direction, respectively, with the two walls of the diffuser, which are the body of rotation and between which the blades are held essentially in the radial direction.

The prior art method, consisting in the formation of directing vanes and diffuser independently of one another in order to best optimize their shape, their dimensions and their functions, and then fixing by means of suitable in this case, means securing the rear downstream end of the directing vanes on the front downstream end of the diffuser. However, in this case, the fastening means used are quite heavy and bulky and can create a head loss to sweat the ka of air through the device.

There is also known a method consisting in forming a rectifying device and a diffuser in the form of a single part. However, the possibilities of this technology are very limited as it does not allow to optimize the functions of these devices and to form a rectifying apparatus of complex shape, in particular a rectifying devices containing a large number of blades, with small radial dimensions (for example, a rectifying device having more than 100 blades). In particular, it is extremely difficult to implement methods foundry straightener apparatus and a diffuser in the form of a single part, as foundry cores which are provided between the vanes directing vanes and radial walls of the diffuser are difficult to access, due to which it becomes very difficult, and sometimes impossible, extraction of these cores.

The technical task of the present invention is to provide a relatively simple, economical and effective solutions to these problems by creating a guide device for air flow.

To solve this task according to the invention proposed a guiding device for the flow of inlet air into the combustion chamber of a gas turbine engine containing a rectifying apparatus and positioned behind him diffuser, and spams the speaker apparatus includes two coaxial shells, between which the blades are held essentially in the radial direction, and a diffuser contains two coaxial walls, which are the body of rotation and connected to each other by means of radial partitions, the device characterized by the fact that one of the shells directing vanes formed as a single part with one represents the body rotation of the wall of the diffuser, and the other sides of this directing vanes attached and fixed to the other represents the body rotation of the wall of the cone and vanes directing vanes are rigidly connected by its end to one side of this straightener apparatus and are with some small clearance from the other shells on his other end.

In accordance with the invention only one of the shells directing vanes formed as a single part with a diffuser, and the other sides, directing vanes attached and fixed, for example, by welding on the diffuser so that the device has been cased. Thus, the device in accordance with the proposed invention does not require the use of special fastening means, which are quite heavy and bulky, which reduces the overall weight of the device and not to limit the aerodynamic who Yu guiding function of this device with respect to the air flow.

Thus, the proposed device is a compromise between different used to date manufacturing technologies and it allows you to optimize performed by this device functions while maintaining the relative ease of manufacture. In particular, the shape and dimensional parameters of a straightening apparatus can be optimized irrespective of the form and dimensional parameters of the cone and they are not limited by the method of manufacturing this device, and a rectifying device may be quite complex and may have a small radial size and a sufficiently large number of blades. For example, in the case when one of the shells directing vanes and diffuser formed as a single casting with vanes directing vanes and radial walls of the diffuser, foundry cores are easily available to remove them due to the lack of other shells directing vanes.

In summary, the proposed invention allows for savings in the manufacture of shells directing vanes, because the shell comes out of the foundry, along with a diffuser. The invention can also provide savings in the manufacture of blades of a straightening apparatus in the case where the blades are manufactured by casting instead of the ones with a diffuser.

In addition, the device in accordance with the invention is simpler to manufacture and install and can provide a significant gain in weight compared to existing devices. The proposed device also allows you to reduce the risk of inadequate compliance, reduce manufacturing time and improve reliability because the system is formed of a rectifying device and a diffuser, ultimately turns out to be cased.

In accordance with another feature of the invention the outer shell of a rectifying device and a represents the body rotation, the outer wall of the diffuser is formed as one part and the end of the inner shell directing vanes attached, for example, by welding on the front downstream end represents the body rotation of the inner diffuser wall.

In accordance with one variant of implementation of the present invention vanes directing vanes are rigidly connected by their outer radial ends with the outer shell of a straightening apparatus and separated a small radial clearance from the inner shells of this straightening device.

As embodiments, vanes directing vanes are rigidly connected by its inner radial direction to nzami with an inner shell of a straightening apparatus and separated by a small radial clearance from the outer shell of this straightening device.

The gap between the blades and cowling directing vanes has a value contained in the operation in the range from 0.1 mm to 0.5 mm

The blades are rigidly attached to the shell of a straightening apparatus by inserting and fixing, for example, by soldering one end of these blades in the corresponding slot provided in the cowling. Thus, the blades can be optimized and implemented independently from the shell in which they are installed.

As a variant implementation, the blades are formed as one piece with the shell of a straightening apparatus. In the case when the shell is an outer shell directing vanes, the vanes are formed at the same time as the diffuser.

The inner shell of a straightening apparatus preferably includes an annular axial projection that interacts with representing the body of rotation of the inner wall of the diffuser, in order to facilitate the positioning and securing of this shell on the cone.

The present invention relates also to a diffuser for a gas turbine engine, comprising two coaxial and represents the body rotation of the wall that are related to each other by means of radial partitions, the diffuser is characterized by the fact that one of the representing body of rotation of the walls of the diffuse Pat tern of the RA continues in his front stream side in the axial direction beyond the other of these represents the body rotation of the wall of the diffuser, to form the shell of a straightening device designed for placement in the axial direction of flow in front of the diffuser.

In accordance with one variant of implementation of the continuation of the wall directing vanes in the direction against the flow contains many cross-cutting radial slits, evenly distributed around the axis of the cone. The number of these gaps, for example, is more than 100.

Alternatively, implementation, continuation in the direction against the flow wall directing vanes formed in a single piece with radial vanes uniformly distributed around the axis of the cone. The number of these blades, for example, is more than 100.

The present invention relates also to the ring for directing vanes of a gas turbine engine, characterized in that it is formed as a single part with the blades passing in the radial direction from the cylindrical surface of the shell and evenly distributed around the axis of the shell.

In addition, the present invention relates to a cowling for directing vanes of a gas turbine engine, characterized in that it contains many cross-cutting radial slits, evenly distributed around the axis of this shell.

In addition, the present invention relates to the blade on which I am directing vanes of a gas turbine engine, containing the front edge and the rear edge of the flow of the gas stream, characterized in that it contains in one of its longitudinal ends, the tool is inserted into the corresponding slit shells directing vanes in a direction essentially parallel to the longitudinal axis of the scapula.

Finally, the present invention relates to gas turbine engines, such as aircraft turbojet or turboprop engine, characterized in that it contains a device of the type indicated above.

Other details, features and advantages of the invention will be better understood from the following description of non-restrictive examples of its implementation, where references are given in the Annex to this description of the drawings, in which:

figure 1 depicts a schematic axial section of a sending device for air flow, according to the invention;

2 is a diagram of part of a sending device according to the invention;

figure 3 - General view of the embodiments of the device, if you look at it front on the flow and in the absence of internal shell of a straightening apparatus according to the invention;

4 is a perspective view of the device shown in figure 3, according to the invention;

5 is a diagram of part of the guide device in figure 2, another embodiment is proposed to the constituent of the invention;

figa diagram of the parts of the device, according to the invention;

6 is a perspective view of the device figure 5 in the front view according to the flow and in the absence of the inner shell and the blades of a straightening apparatus according to the invention;

7 is a General view of part of a straightening apparatus of figure 6, according to the invention;

Fig - General view of embodiments of a straightening apparatus according to the invention.

The device 10 (Fig 1) in accordance with the invention installed in the axial direction between the compressor (not shown)located at the flow front of the device, and the camera 12 of the combustion gas turbine engine, in order to ensure the flatness and the appropriate orientation of the air flow coming out of the compressor, and the power of the air chamber 12 of the combustion, which in turn feeds the gas turbine (not shown)located downstream behind the combustion chamber.

The device 10 includes, when viewed from front to back on the flow straightener device 14 and the diffuser 16, which are connected with each other and hold the outer conical shell 18, which is held in an outward direction against the flow of the stream and which is fixed by an external annular flange 20 on the outer casing 22 of the combustion chamber and using the internal conical shell 24, which runs in the direction of inside the course of Patoka which is fixed with the inner annular flange 26 on the inner cover 28 of the camera 12 combustion.

On the outer casing 22 of the combustion chamber installed the injectors 30 fuel evenly circumferentially distributed around the longitudinal axis of the combustion chamber and opening at their inner radial direction of the end inside this combustion chamber. The fuel injected into the combustion chamber, is intended for mixing with the air leaving the device 10, and for ignition and combustion, and then ejection of the gaseous combustion products to the turbine to bring into rotational motion of the shaft of the gas turbine engine.

The diffuser 16 contains a represents the body rotation of the inner wall 32 that is associated with the inner conical shell 24, and represents the body rotation of the outer wall 34 that is associated with the outer conical shell 18, the walls 32 and 34 are interconnected by means of radial partitions 36, the number of which is, for example, 18 pieces.

A rectifying unit 14 includes an inner shell 38, which in the axial direction is the same line representing a body of rotation of the inner wall 32 of the diffuser, the outer shell 40, which is axially located on the same line represents the body rotation of the outer wall 34 of the diffuser, and the blades 42, which are held in the radial direction between the inner shell 32 of the outer shell 40 of a straightening apparatus. Blade 42 is made, for example, in the amount of 126 units are independent from each other and offset in the axial direction against the flow stream relative to the radial walls 36 of the cone.

In the implementation presented in figure 1 and 2, the outer shell 40 and blade 42 directing vanes 14 are formed in a single piece with the outer wall 34 of the diffuser 16. The inner shell 38 directing vanes attached to its rear downstream end, for example, by means of a welded seam 44 in the front on the thread end of the inner wall 32 of the diffuser, and this shell is separated from the interior in the radial direction of the end of each blade 42 small radial clearance 46. Blades 42 and the outer shell 40 of a straightening apparatus is fabricated as a single molded part with a diffuser 16. The inner diameter of the shell 38 at its rear downstream end is equal to the inner diameter of the wall 32 of the diffuser on her front on the thread end.

Radial clearance 46 between the inner radial ends of the vanes and the inner cowling directing vanes may vary in the range from 0.1 mm to 0.5 mm during engine operation due to thermal expansion and centrifugal efforts, the effects of which are vanes 42 and shells 38, 40 directing vanes.

In accordance with a variant implementation is AI vanes 42 (Fig. 3 and 4) is fixed with its outer radial ends 48 on the outer shell 40 of a straightening apparatus, which has always formed as one piece with the diffuser 16. Interior in the radial direction, the ends 50 of the blades are separated by a small radial clearance 46 from the inner shell (not shown) directing vanes, which is fixed by welding on the front on the thread end 51 of the inner wall 32 of the diffuser.

Vanes 42 typically contain lower surface 52 or the inner concave surface and an upper surface 54, or the outer convex surface, which are interconnected at the front by the thread ends on the front edge 56 of the blade and on the back on the thread ends at the trailing edge 58 of the blade. Blade realized, for example, by using the technology of the ESM (ltr hmil hining).

Outside in the radial direction of the end part of each blade forming means 48 is inserted into the corresponding slot 60 provided in the outer shell 34 of a straightening apparatus. Slots 60 are essentially radial and end-to-end and they are uniformly distributed around the axis of the shell. Means 48 of the insertion blades are inserted into the slot 60 in a substantially radial direction and are held in this gap, for example, using prepaymania outside in the radial direction of the end of the blade to the outer cylin the historical surface of the shell 40. Slit 60 may be formed during casting or can be obtained from laser cut in the shell.

In accordance with a specific example of implementation of the vanes 42 are fixed by jamming in a predetermined position in the slots 60 of the shell by means of solder balls (diameter which is, for example, 1 mm), which melt point manually or by electric discharge between the outer radial ends of the blades and the outer cylindrical surface of the shell.

In accordance with another variant of realization of the vanes 42 (figure 5-8) directing vanes are rigidly connected by their inner radial ends with the inner shell 38 of a straightening apparatus that is attached and fixed his back on stream by the end of on the front on the thread end of the inner wall 32 of the diffuser. The outer shell 40 of a straightening apparatus is formed as one piece with the diffuser 16 and separated by a small radial clearance from the outside in the radial direction of the ends of each of the blades.

As shown in Fig.7, the blades 42 and the inner shell 38 directing vanes formed in a single piece using appropriate technologies, such as casting, technology D (ltr Dishrg hining), high-speed milling, etc.

As a variant of the implementation of the internal in the radial direction, the ends 62 (Fig) blades 42 are inserted and fixed in the respective radial slots 64 of the inner shell. These blades similar to the blades described above with reference to Fig. 3 and 4, and the slit 64 in the ring are cross-cutting and uniformly distributed around the axis of the shell. The inner radial ends of the blades can be fixed by soldering on the inner cylindrical surface of shell 38.

The inner shell 38 of a straightening apparatus preferably includes an axial annular ledge 66 of centering (figa)designed for insertion in the inner radial part of the inner diffuser wall to facilitate mounting of the shell. The shell 38 is in this case mounted on the wall 32 of the diffuser by means of welding the rear downstream end of the circular protrusion 66 to the inner cylindrical surface of wall 32 to eliminate the protrusion of spot welds or weld in the direction of inside and to prevent the disturbance of the flow of the air flow in this device. The inner shell 38 of each of the above devices may also have an axial circular protrusion 62.

In the examples of implementation in Fig. 4, 5 and 6, the diffuser 16 contains the separator 70, which is fixed on the radial walls 36 of the cone between its inner wall 32 and outer wall 34 and the separator performs the function of separating the gas stream emerging from the directing vanes, two annular coaxial with the Rui.

A rectifying unit 14 and the diffuser 16 is made, for example, from an alloy based on Nickel and chromium.

1. Guiding device for flow of inlet air into the combustion chamber of a gas turbine engine containing a rectifying apparatus and located behind the diffuser and straightening apparatus includes two coaxial shells, between which is placed the blade passing essentially in the radial direction, and a diffuser contains two coaxial walls, which are the body of rotation and connected to each other by means of radial partitions, wherein one of the shells directing vanes formed as a single part with one represents the body rotation of the wall of the diffuser, and the other sides, directing vanes attached and fixed on the other representing body rotation of the wall of the diffuser with vanes directing vanes are rigidly connected at one end with one side of a straightening apparatus and separated with a small gap from the other shell at the other end.

2. The device according to claim 1, characterized in that the outer shell of a rectifying device and a represents the body rotation, the outer wall of the diffuser is formed as one part and the end of the inner shell directing vanes attached by welding to the forward flow con the e represents the body rotation the inner wall of the cone.

3. The device according to claim 2, characterized in that the outer shell of a straightening device is made by casting as a single part together with the diffuser.

4. Device according to any one of claim 2 or 3, characterized in that the rear downstream end of the inner shell of a straightening apparatus is fixed by welding on the front downstream end represents the body rotation of the inner diffuser wall.

5. The device according to claim 2, characterized in that the vanes directing vanes are rigidly connected by their outer radial ends with the outer shell of a straightening apparatus and separated a small radial clearance from the inner shells of a straightening device.

6. The device according to claim 2, characterized in that the vanes directing vanes are rigidly connected by their inner radial ends with an inner shell of a straightening apparatus and separated by a small radial clearance from the outer shell of a straightening device.

7. Device according to any one of subparagraph 5 or 6, characterized in that the blades are rigidly attached to the shell of a straightening apparatus by inserting and fixing by soldering one end of the blades in the corresponding slot provided on the ring.

8. Device according to any one of subparagraph 5 or 6, characterized in that the vanes are formed in one piece with the shell JV is allaudio apparatus.

9. The device according to claim 2, characterized in that the inner shell of a straightening apparatus includes an annular axial projection inserted in the radial direction in the inner part represents the body rotation of the inner diffuser wall.

10. The device according to claim 1, characterized in that the clearance between the blades and cowling directing vanes during operation has a value in the range from about 0.1 mm to 0.5 mm

11. Gas turbine engine, such as aircraft turbojet or turboprop engine, wherein the engine includes a device in accordance with one of claims 1 to 10.

12. Diffuser for a gas turbine engine, comprising two coaxial and represents the body rotation of the wall that are related to each other by means of radial partitions, wherein one of the representing body rotation of the wall of the cone continues in his front stream side in the axial direction beyond the other of these represents the body rotation of the wall of the cone to form the shell of a straightening device intended for placement in the axial direction of flow in front of the diffuser.

13. The diffuser according to item 12, characterized in that the continuation in the direction against the flow straightener wall unit contains many skvoz what's radial slots, uniformly distributed around the axis of the cone.

14. The diffuser according to item 12, characterized in that the continuation in the direction against the flow wall directing vanes formed in one piece with radial vanes uniformly distributed around the axis of the cone.

15. The diffuser according to any one of p or 14, characterized in that the continuation in the direction against the flow straightener wall unit contains more than 100 slots or radial blades.