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CN-224214233-U - Turbine rotor blade, turbine rotor and engine turbine

CN224214233UCN 224214233 UCN224214233 UCN 224214233UCN-224214233-U

Abstract

The utility model discloses a turbine rotor blade, a turbine rotor and an engine turbine, belongs to the technical field of turbine engines, and is used for solving the problem of insufficient connection strength of a root extension and a tenon caused by overweight blade weight of the turbine. The turbine rotor blade comprises a cavity, wherein the cavity is positioned inside the blade and penetrates through the blade in the radial direction, an opening is formed in one end of the cavity, which is positioned at a blade tip, the other end of the cavity is closed, the cavity sequentially comprises a first cavity section, a second cavity section, a third cavity section and a fourth cavity section in the radial direction of the blade, the first cavity section and the second cavity section are arranged in the center of the inside of a tenon, the third cavity section and the fourth cavity section are respectively arranged inside a root extension part and a blade body and are respectively matched with the shapes of the root extension part and the blade body, and the chord width of the first cavity section and the second cavity section along the blade is smaller than the chord width of the third cavity section along the blade. The turbine rotor blade effectively combines the strength and the rigidity of the blade, and improves the overall performance of the engine turbine.

Inventors

  • WANG ZHIGUO
  • WANG TONG
  • JIA HAIYAN
  • SUN ZHANLEI

Assignees

  • 成都镧动科技有限公司

Dates

Publication Date
20260508
Application Date
20250710

Claims (10)

  1. 1. A turbine rotor blade, characterized by comprising a cavity (1); the cavity (1) is positioned in the blade and penetrates through the blade in the radial direction, one end of the cavity (1) positioned at the blade tip is provided with an opening (101), and the other end of the cavity (1) is closed; The cavity (1) sequentially comprises a first cavity section (11), a second cavity section (12), a third cavity section (13) and a fourth cavity section (14) along the radial direction of the blade; the first cavity section (11) and the second cavity section (12) are arranged in the center of the inside of the blade tenon; The third cavity section (13) and the fourth cavity section (14) are respectively arranged in the root extending part and the blade body and are respectively matched with the shapes of the root extending part and the blade body, and the inner diameter of the fourth cavity section (14) gradually decreases from the blade tip to the blade root; The chord-wise width of the first cavity section (11) and the second cavity section (12) along the blade is smaller than the chord-wise width of the third cavity section (13) along the blade.
  2. 2. Turbine rotor blade according to claim 1, wherein the second cavity section (12) has a chord-wise width along the blade which is less than 1/3 of the chord-wise width of the third cavity section (13).
  3. 3. Turbine rotor blade according to claim 2, wherein the first cavity section (11) has a smaller chord-wise width along the blade than the second cavity section (12).
  4. 4. Turbine rotor blade according to claim 1, further comprising a blocking piece (2), the blocking piece (2) being fixed to the end of the blade tenon for blocking one end of the first cavity section (11).
  5. 5. Turbine rotor blade according to any of claims 1 to 4, further comprising a first rib (3) provided on the inner wall of the cavity (1), said first rib (3) being located in the first cavity section (11) and the second cavity section (12) perpendicular to the chord direction of the blade.
  6. 6. Turbine rotor blade according to claim 5, wherein the first rib (3) extends to the third cavity section (13).
  7. 7. Turbine rotor blade according to claim 1, further comprising a second rib (4) provided on the inner wall of the cavity (1), said second rib (4) being located in said fourth cavity section (14) and perpendicular to the radial direction of the blade.
  8. 8. Turbine rotor blade according to claim 7, wherein at least two second ribs (4) are arranged at intervals in the radial direction of the blade.
  9. 9. A turbine rotor comprising a turbine rotor disc (20), a turbine neck (30) and turbine rotor blades (10) according to any one of claims 1 to 8.
  10. 10. An engine turbine comprising the turbine rotor of claim 9.

Description

Turbine rotor blade, turbine rotor and engine turbine Technical Field The utility model belongs to the technical field of aeroengines, and relates to a turbine rotor blade, a turbine rotor and an engine turbine. Background High pressure turbine blades are the main components of high pressure turbines, which are directly subjected to the washout of high temperature and high pressure gases, playing the role of converting the gas potential energy into the mechanical energy of the core rotor rotating at high speed, and therefore, high pressure turbine blades tend to be subjected to very severe combined aerodynamic, thermal and mechanical loads which determine the life of the high pressure turbine blades, which directly determine the life of the aeroengine. The high-pressure turbine of the medium-sized and small-sized aeroengine has higher rotating speed, usually tens of thousands or even hundreds of thousands of revolutions, the mass of the blade is increased by one gram under the action of the high rotating speed, the centrifugal load is usually increased by thousands of newtons, and the centrifugal load brings great challenges to the connection strength of the blade extending root and tenons. Because the pneumatic modeling of the blades is completed and the number of the blades is determined, the axial dimension of the tenon joint is lengthened to obtain strength reserve, and the excessive increase of the axial dimension of the tenon joint increases the mass of the whole rotor system, so that other risks are brought. Disclosure of utility model In view of the above analysis, the present utility model is directed to providing a turbine rotor blade, a turbine rotor, and an engine turbine, to solve the technical problem of insufficient connection strength of the root extension and the tenon due to the excessive weight of the blade of the turbine. The aim of the utility model is mainly achieved by the following technical scheme. The utility model provides a turbine rotor blade, which comprises a cavity, wherein the cavity is positioned in the blade and penetrates through the blade in the radial direction, one end of the cavity, which is positioned at a blade tip, is provided with a cavity opening, the other end of the cavity is closed, the cavity sequentially comprises a first cavity section, a second cavity section, a third cavity section and a fourth cavity section along the radial direction of the blade, the first cavity section and the second cavity section are arranged in the center of the inside of a tenon of the blade, the third cavity section and the fourth cavity section are respectively arranged in the root extension and the blade body and are respectively matched with the shapes of the root extension and the blade body, the inner diameter of the fourth cavity section gradually reduces from the blade tip to the blade root, the cavity opening is smaller than the inner diameter of the fourth cavity section, and the chord width of the first cavity section and the second cavity section along the blade is smaller than the chord width of the third cavity section along the blade. Further, the chord-wise width of the second cavity section along the blade is less than 1/3 of the chord-wise width of the third cavity section along the blade. Further, the chord-wise width of the first cavity section along the blade is smaller than the chord-wise width of the second cavity section along the blade. Further, the device further comprises a blocking piece, wherein the blocking piece is fixed to the end portion of the blade tenon and used for blocking one end of the first cavity section. Further, the blade further comprises a first rib plate arranged on the inner wall of the cavity (1), and the first rib plate is positioned in the first cavity section and the second cavity section and perpendicular to the chord direction of the blade. Further, the first rib (3) extends to said third cavity section (13). Further, the novel air conditioner further comprises a second rib plate arranged on the inner wall of the cavity (1), and the second rib plate is positioned in the fourth cavity section and perpendicular to the radial direction of the blade. Further, at least two second ribs are arranged at intervals in the radial direction of the blade. In a second aspect of the utility model, there is provided a turbine rotor comprising a turbine rotor disk, a turbine neck and any of the turbine rotor blades provided in the first aspect of the utility model. In a third aspect of the utility model, there is provided an engine turbine comprising the turbine rotor provided in the second aspect of the utility model. Compared with the prior art, the utility model has at least one of the following beneficial effects: 1. According to the turbine rotor blade, the cavity is arranged in the blade, and the third cavity section and the fourth cavity section are respectively matched with the shapes of the extending root and the blade body, so that t