Jet engine turbine blade

Abstract

To solve the problems that conventional film cooling members have a cylindrical shape with rounded edges at its front and rear, which reduces air resistance to some extent, and that they also have a rounded edge and a slender rear.SOLUTION: A film cooling member is formed into a diamond-shaped cylindrical shape, to reduce air resistance. Further, turbine blades also has a sharply horn-like edge, to cut through the air, thereby reducing air resistance.SELECTED DRAWING: Figure 2

Description

[Technical Field]

[0001] In this invention, air Airl1, Airl2, and Airl3 are compressed in the compressor in the cold section CS and sent to the hot section HS of the turbine (Fig. 1). Air is sent to the turbine TURBIN and jet fuel is burned to generate a jet stream. Exhaust jets COAir1, COAir2, and COAir3 are discharged rearward as jet streams EXAir, providing thrust for the jet aircraft (Fig. 1). [Background technology]

[0002] The conventional turbine mechanism is composed of multiple disks with film cooling elements and turbine blade elements arranged around the circumference of multiple disks. The conventional film cooling elements have an elongated cylindrical shape through which air flows. The turbine blades are vane-shaped with a rounded front and holes. Summary of the Invention [Problem to be solved by the invention]

[0003] The conventional film cooling element has a cylindrical shape with rounded edges at the front and rear, which reduces air resistance to some extent. Also, the tip is rounded and the rear is elongated.

[0004] The solution to this problem is to make the film cooling element diamond-shaped, which reduces air resistance (Fig. 3).Furthermore, the tip of the turbine blade is sharpened in a mountain shape, which cuts through the air, reducing air resistance (Fig. 11).

[0005] For example, the film cooling element (FCOL) has been designed to have a diamond-shaped cylindrical shape, with air flowing in from the flange plate 12 (Fig. 3) on the lower surface and expelling the air from multiple holes on the surface of the film cooling element, which are arranged around the circumference, reducing the air resistance of the film cooling element (FCOL).

[0006] The turbine blade (TBB) has a square tip and tapers towards the rear. Air enters Air1 and Air2 (Fig. 15) from the mounting bracket 121 provided under the turbine blade (TBB) and is discharged from the hole Ho on the front of the turbine blade TBB (Fig. 11). The turbine blade TBB is arranged circumferentially (Fig. 19) to reduce air resistance and rotates at high speed. Effects of the invention

[0007] In the present invention, film cooling elements become hot due to the combustion of jet fuel. As a result, turbine blades rotate at high speeds and must withstand centrifugal force, which places a heavy load on them. This causes creep, which gradually distorts the blades and leads to breakage. The film cooling elements of the present invention are arranged alternately with the turbine blades, and air is injected from holes on the surface of the film cooling elements to cool the hot turbine blades. This design prevents creep and efficiently cools the turbine blades.

[0008] In this invention, turbine blades reach high temperatures due to the combustion of jet fuel. As the turbine blades rotate at high speeds, they must withstand centrifugal force, which places a heavy load on them. This causes creep, which gradually distorts the blades and leads to breakage. However, this invention is designed to be strong enough to prevent creep and ensure no breakage occurs. [Brief explanation of the drawings]

[0009] [Figure 1] Simplified perspective view of a jet engine [Figure 2] Simplified perspective view of turbine [Figure 3] Film cooling perspective view [Figure 4] Film cooling left side view [Figure 5] Film cooling right side view [Figure 6] Film cooling rear view [Figure 7]Film cooling front view [Figure 8] Film cooling plan view [Figure 9] Film cooling bottom view [Figure 10] Film cooling assembly perspective view [Figure 11] Perspective view of a turbine blade [Figure 12] Rear perspective view of turbine blade [Figure 13] Turbine blade left side view [Figure 14] Right side view of turbine blade [Figure 15] Turbine blade front view [Figure 16] Turbine blade rear view [Figure 17] Turbine blade plan view [Figure 18] Turbine blade bottom view

figure

[0010] In Figure 1, the simplified jet engine diagram is first divided into a cold section (CS) and a hot section (HS). Behind the hot section (HS), the jet stream (EXAir) is released.

[0011] In the cold section CS, air is drawn in from the front of the jet engine, and compressed air is generated by Air1, Air12, Air13, and the compressor COMP, which then sends it into the combustion chamber.

[0012] In the hot section HS, the compressor COMP ignites compressed air in the combustion chamber to rotate the turbine TURBINE. The rotating turbine TURBINE sends exhaust jets COAir1, COAir2, and COAir3 rearward to generate the jet stream EXAir, which provides the thrust for the jet aircraft.

[0013] Regarding Figure 2, Figure 2 shows a schematic perspective view of the turbine TURBINE. The turbine TURBINE has multiple film cooling components arranged on a disk, A1, A2, and A3. The turbine blade TBB has multiple turbine blade components arranged on a disk, B1, B2, and B3.

[0014] The turbine in the hot section HS rotates in the direction of rotation RO on the shaft axis SF. The disk attached to the shaft is hollow, and air Air1, Air2, and Air3 compressed by the compressor COMP (Fig. 1) are injected into the hollow of the disk from the shaft, causing it to rotate at high speed.

[0015] To explain the hot section a little more, the compressed air is mixed with jet fuel and combusted by an ignition device, causing the turbine to rotate at high speed.

[0016] 3, 4, 5, 6, and 7, the film cooling member FCOL consists of a film cooling body 100, a plate 10, a cylinder 11, and a flange plate 12. The film cooling has multiple holes on both side surfaces LCOLAir and RCOLAir (Figs. 6, 7, and 8), and air 55 (Figs. 4 and 9) is injected from the bottom of the film cooling body, and cooling air COLAir is output from the holes on both side surfaces of the film cooling body, which rotates at high speed.

[0017] In Figure 10, multiple film cooling elements are attached to the rotating disk at A1, A2, and A3 of the turbine TURBINE. It rotates at high speed around the axis SF2. Compressed air is output from inside the axis to A1, A2, and A3, and is then output from the sides of the film cooling elements FCOL as air RCOLAir and LCOLAir (Figures 4, 5, 6, 7, and 8).

[0018] The film cooling element FCOL (Fig. 3) serves to cool the turbine blade TBB (Fig. 11) which is rotating at high speed and is in a high temperature state, thereby protecting it from fracture.

[0019] 11 and 12, the turbine blade TBB has a triangular front surface with a hole Ho. The interior is hollow. The blade is made up of a main body, a plate 101, a flange 111, and a mounting fixture 121.

[0020] Turbine blades TBBs must be heat resistant because they rotate at high speeds and high temperatures. The materials used for turbine blades TBBs are manufactured using special methods, such as single crystal heat-resistant alloys. Specific materials used are iron-, nickel-, or cobalt-based alloys. Furthermore, the crystals of these alloys must be delicately crafted. The surface of turbine blades TBBs is often coated with a special heat-resistant coating to prevent corrosion at high temperatures.

[0021] The turbine blade TBB rotates at high speed and must withstand centrifugal force Cenl, so it is subjected to a heavy load. As the turbine blade TBB continues to be subjected to load for a long time, a phenomenon called creep occurs, causing it to gradually become distorted. If this continues for a long time, it may break, and this phenomenon becomes more pronounced at high temperatures.

[0022] As shown in Figures 13 and 14, the inside of the turbine blade TBB is hollow. There are many holes Ho on the front, like holes made by pins. These holes Ho require an extremely high level of technology and are very costly.

[0023] The direction of rotation of the turbine blade TBB generates a strong centrifugal force Cenl at the front of the triangular shape (Fig. 17). Therefore, it is shaped to reduce air resistance.

[0024] The turbine blade TBB is cooled by air Air, Air1, and Air2 (Figures 15, 16, and 18).

[0025] In Figure 19, multiple turbine blades B1, B2, and B3 (TBB) are attached to a rotating disk. They rotate at high speed RO2 around an axis SF3.

[0026] As such, the above-described embodiments are merely illustrative in all respects and should not be construed as limiting. Furthermore, all forms and modifications that fall within the scope of the claims and equivalents are within the scope of the present invention. [Industrial Applicability]

[0027] The present invention is based on the idea that turbine blades reach high temperatures due to the combustion of jet fuel. As the turbine blades rotate at high speeds, they must withstand centrifugal force, which places a heavy load on them. This causes a phenomenon known as creep, which gradually distorts the blades and causes them to break. However, the design prevents this from happening. The film cooling of the present invention also maintains a design that makes the turbine blade less susceptible to creep, preventing breakage. [Explanation of symbols]

[0028] CS Cold Section HS Hot Section COMP Compressor TURBINE Air Air1, Air2, Air3 EXAir Jet Stream FCOL Film Cooling Material 100 Film cooling body 10 plates 11 tubes 12 flange plate 55 Air COLAir, LCOLAir, RCOLAir air COAir1, COAir2, COAir3 exhaust jet TBB turbine blade Ho hole A1, A2, A3 disc film cooling material SF shaft axis RO1 High-speed rotation 101 Plate 111 flange 121 Mounting hardware Cenl, CenlL, CenlR centrifugal force B1, B2, B3 disk turbine blades SF3 shaft RO2 High-speed rotation

Claims

1. In the wing section, plate section and flange section, The upper part of the wing is characterized by a diamond-shaped wing. Film cooling blades

2. In the wing section, plate section and flange section, The wing portion is characterized by a front mountain-shaped wing. Turbine blades

3. In the wing section, plate section and flange section, The blade portion is made of two or more metal elements. The turbine blade according to claim 2.

4. In the wing section, plate section and flange section, The blade portion is characterized by being heat-resistant coated. The blade according to claim 1, claim 2, or claim 3

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