KR980002707A - Cooling blades of turbine - Google Patents

Cooling blades of turbine Download PDF

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Publication number
KR980002707A
KR980002707A KR1019960022005A KR19960022005A KR980002707A KR 980002707 A KR980002707 A KR 980002707A KR 1019960022005 A KR1019960022005 A KR 1019960022005A KR 19960022005 A KR19960022005 A KR 19960022005A KR 980002707 A KR980002707 A KR 980002707A
Authority
KR
South Korea
Prior art keywords
cooling
pressure surface
suction surface
insert tube
suction
Prior art date
Application number
KR1019960022005A
Other languages
Korean (ko)
Other versions
KR100252628B1 (en
Inventor
권기훈
손정욱
박준태
Original Assignee
이대원
삼성항공산업 주식회사
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by 이대원, 삼성항공산업 주식회사 filed Critical 이대원
Priority to KR1019960022005A priority Critical patent/KR100252628B1/en
Publication of KR980002707A publication Critical patent/KR980002707A/en
Application granted granted Critical
Publication of KR100252628B1 publication Critical patent/KR100252628B1/en

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/186—Film cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/202—Heat transfer, e.g. cooling by film cooling

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

앞전(26)과 뒷전(28)쪽에 충돌구멍(18)이 형성된 인서트 튜브(16)를 내부에 설치하고, 냉각공기를 인서트튜브(16)와 압력면(24) 및 흡입면(22) 사이의 공간(23)으로 공급하여 압력면(24)과 흡입면(22)에 대한 대류냉각을 행하고, 흡입면(22)과 압력면(24)에 대한 대류냉각을 행한 냉각공기를 인서트튜브(16)로 유입하여 앞전(26)과 뒷전(28)에 대한 충돌냉각과 막냉각을 행하는 터빈의 냉각 블레이드를 제공한다.An insert tube 16 having an impingement hole 18 formed at the front side 26 and the rear side 28 is provided therein, and cooling air is inserted between the insert tube 16 and the pressure surface 24 and the suction surface 22. Cooling air that is supplied to the space 23 to perform convection cooling on the pressure surface 24 and the suction surface 22, and performs convection cooling on the suction surface 22 and the pressure surface 24. The insert tube 16 It provides a cooling blade of the turbine which flows into and performs impingement cooling and film cooling for the leading edge 26 and the trailing edge 28.

상기한 압력면(24)과 흡입면(22)의 대류냉각 효율을 향상시키기 위하여 내면에 형성하는 리브(32)를 불연속되는 직선형상으로 형성하는 것이 바람직하다. 그리고 상기한 리브(32)를 서로 다른 원주상에 위치하도록 형성하여도 좋다.In order to improve the convective cooling efficiency of the pressure surface 24 and the suction surface 22, the rib 32 formed on the inner surface is preferably formed in a discontinuous linear shape. The ribs 32 may be formed to be positioned on different circumferences.

Description

터빈의 냉각 블레이드Cooling blades of turbine

본 내용은 요부공개 건이므로 전문내용을 수록하지 않았음Since this is an open matter, no full text was included.

제1도는 본 발명 터빈의 냉각 블레이드의 일실시예가 적용된 가스 터빈 엔진을 개략적으로 나타내는 단면도.1 is a cross-sectional view schematically showing a gas turbine engine to which an embodiment of a cooling blade of a turbine of the present invention is applied.

제2도는 본 발명 터빈의 냉각 블레이드의 일실시예를 나타내는 사시도.2 is a perspective view showing one embodiment of a cooling blade of the turbine of the present invention.

제3도는 제2도의 A-A 면도.3 is the shaving A-A of FIG.

Claims (3)

앞전과 뒷전쪽에 충돌구멍이 형성된 인서트튜브를 내부에 설치하고, 냉각공기를 인서트튜브와 압력면 및 흡입면 사이의 공간으로 공급하여 압력면과 흡입면에 대한 대류냉각을 행하고, 흡입면과 압력면에 대한 대류냉각을 행한 냉각공기를 인서트튜브 안으로 유입하여 앞전과 뒷전에 대한 충돌냉각과 막냉각을 행하는 터빈의 냉각 블레이드.An insert tube with a collision hole formed at the front and rear sides is installed inside, and the cooling air is supplied to the space between the insert tube and the pressure surface and the suction surface to conduct convection cooling to the pressure surface and the suction surface. Cooling blades in turbines that introduce convective cooling air into the insert tube and impinge the cooling and film cooling on the front and back sides. 제1항에 있어서, 상기한 압력면과 흡입면의 대류냉각 효율을 향상시키기 위하여 내면에 형성하는 리브를 불연속되는 직선형상으로 형성하는 터빈의 냉각 블레이드.The turbine cooling blade according to claim 1, wherein the ribs formed on the inner surface are formed in a discontinuous linear shape in order to improve the convective cooling efficiency of the pressure surface and the suction surface. 제1항에 있어서, 상기한 압력면과 흡입면의 대류냉각 효율을 향상시키기 위하여 내면에 형성하는 리브를 서로 다른 원주상에 위치하도록 형성하는 터빈의 냉각 블레이드.The cooling blade of claim 1, wherein ribs formed on the inner surface of the pressure surface and the suction surface are formed on different circumferences to improve convective cooling efficiency of the pressure surface and the suction surface. ※ 참고사항 : 최초출원 내용에 의하여 공개하는 것임.※ Note: The disclosure is based on the initial application.
KR1019960022005A 1996-06-18 1996-06-18 Cooling blade of a turbine KR100252628B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
KR1019960022005A KR100252628B1 (en) 1996-06-18 1996-06-18 Cooling blade of a turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
KR1019960022005A KR100252628B1 (en) 1996-06-18 1996-06-18 Cooling blade of a turbine

Publications (2)

Publication Number Publication Date
KR980002707A true KR980002707A (en) 1998-03-30
KR100252628B1 KR100252628B1 (en) 2000-04-15

Family

ID=19462263

Family Applications (1)

Application Number Title Priority Date Filing Date
KR1019960022005A KR100252628B1 (en) 1996-06-18 1996-06-18 Cooling blade of a turbine

Country Status (1)

Country Link
KR (1) KR100252628B1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR100900810B1 (en) * 2007-04-27 2009-06-04 허담 Method for preparing of Korean citrus peel increased of aglycone flavnoid and mixture containing the powder

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR101605074B1 (en) 2014-11-28 2016-03-21 부산대학교 산학협력단 Cooling system for Gas turbine nozzle with cooling system

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR100900810B1 (en) * 2007-04-27 2009-06-04 허담 Method for preparing of Korean citrus peel increased of aglycone flavnoid and mixture containing the powder

Also Published As

Publication number Publication date
KR100252628B1 (en) 2000-04-15

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