Cooled airfoils for a gas turbine engine

• US 5,702,232 A
• Filed: 12/13/1994
• Issued: 12/30/1997
• Est. Priority Date: 12/13/1994
• Status: Expired due to Term

• Current Assignee: United Technologies Corporation (Rtx Corporation)
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: Moore, Robert P.
• Primary Examiner(s): Carone, Michael J.
• Assistant Examiner(s): Wesson, Theresa M.
• Application Number:
  US08/354,299
• Time in Patent Office: 1,113 Days
• Field of Search: 416/90 R, 416/91, 416/92, 416/95, 416/96 R, 416/97 R, 416/97 A, 416/96 A
• US Class Current: 416/95
• CPC Class Codes: F01D 5/186 Film cooling F01D5/187 takes precedence
• CPC Class Codes: F01D 5/187 Convection cooling
• CPC Class Codes: F05D 2260/202 by film cooling

Abstract

An internally cooled airfoil for a gas turbine engine includes a leading edge region, a mid-chord region, a transition region, and a trailing edge region. The mid-chord region has a double wall configuration with the two outer walls and two inner walls. The trailing edge region has a conventional single wall configuration. The transition region has a three wall configuration designed to provide a gradual transition from the four wall configuration to the two wall configuration and to minimize high stresses therein.

Claims

1. An airfoil for a gas turbine engine having a suction side wall on a suction side and a pressure side wall on a pressure side, said pressure side wall and said suction side wall extending from a leading edge to a trailing edge in a chordwise direction, said airfoil having a leading edge region, a mid-chord region, and a trailing edge region, said regions sequentially situated in said chordwise direction from said leading edge to said trailing edge, said mid-chord region having at least one suction side feed passage and at least one pressure side feed passage, said suction side feed passage being disposed on said suction side and bound by said suction side wall and a first inner wall, said pressure side feed passage being disposed between said pressure side wall and a second inner wall, a feed chamber being defined between said first inner wall and said second inner wall, said trailing edge region having at least one trailing edge passage disposed between said pressure side wall and said suction side wall, said airfoil characterized by:

a transition region disposed between said mid-chord region and said trailing edge region, said transition region having a transition feed passage and a transition chamber, said transition feed passage and said transition chamber being separated by said first inner wall extending from said mid-chord region into said transition region in said chordwise direction and bound by said suction side wall and said pressure side wall.

2. An airfoil for a gas turbine engine having a suction side wall on a suction side and a pressure side wall on a pressure side, said pressure side wall and said suction side wall extending from a leading edge to a trailing edge in a chordwise direction, said airfoil having a leading edge region, a mid-chord region, and a trailing edge region, said regions sequentially situated in said chordwise direction from said leading edge to said trailing edge, said mid-chord region having at least one suction side feed passage and at least one pressure side feed passage, said suction side feed passage being disposed on said suction side and bound by said suction side wall and a first inner wall, said pressure side feed passage being disposed between said pressure side wall and a second inner wall, a feed chamber being defined between said first inner wall and said second inner wall, said trailing edge region having at least one trailing edge passage disposed between said pressure side wall and said suction side wall, said airfoil characterized by:

a transition region disposed between said mid-chord region and said trailing edge region, said transition region including a transition chamber, said pressure side feed passage extending into said transition region, said pressure side feed passage extending into said transition region, said pressure side feed passage and said transition chamber being separated by said second inner wall extending into said transition region in said chordwise direction and bound by said suction side wall and said pressure side wall to reduce stress concentration in said airfoil.

3. An airfoil for a gas turbine engine having a suction side wall on a suction side and a pressure side wall on a pressure side, said pressure side wall and said suction side wall extending from a leading edge to a trailing edge in a chordwise direction, said airfoil having a leading edge region, a mid-chord region, and a trailing edge region, said regions sequentially situated in said chordwise direction from said leading edge to said trailing edge, said mid-chord region having at least one suction side feed passage and at least one pressure side feed passage, said suction side feed passage being disposed on said suction side and bound by said suction side wall and a first inner wall, said pressure side feed passage being disposed between said pressure side wall and a second inner wall, a feed chamber being defined between said first inner wall and said second inner wall, said trailing edge region having at least one trailing edge passage disposed between said pressure side wall and said suction side wall, said airfoil characterized by:

a transition region disposed between said mid-chord region and said trailing edge region, said transition region including a transition chamber, said suction side feed passage extending into said transition chamber, said suction side feed passage extending into said transition region, said suction side feed passage and said transition chamber being separated by said first inner wall extending into said transition region in said chordwise direction and bound by said suction side wall and said pressure side wall to minimize stress concentration in said airfoil.

4. An airfoil for a gas turbine engine having a suction side wall on a suction side and a pressure side wall on a pressure side, said pressure side wall and said suction side wall extending from a leading edge to a trailing edge in a chordwise direction, said airfoil having a leading edge region, a mid-chord region, and a trailing edge region, said regions sequentially situated in said chordwise direction from said leading edge to said trailing edge, said mid-chord region having at least one suction side feed passage and at least one pressure side feed passage, said suction side feed passage being disposed on said suction side and bound by said suction side wall and a first inner wall, said pressure side feed passage being disposed between said pressure side wall and a second inner wall, a feed chamber being defined between said first inner wall and said second inner wall, said trailing edge region having at least one trailing edge passage disposed between said pressure side wall and said suction side wall, said airfoil characterized by:

a transition region disposed between said mid-chord region and said trailing edge region, said transition region having a transition feed passage and a transition chamber, said transition feed passage and said transition chamber being separated by said second inner wall extending from said mid-chord region into said transition region in said chordwise direction and bound by said suction side wall and said pressure side wall.