Laminated airfoil and method for turbomachinery

• US 4,221,539 A
• Filed: 04/20/1977
• Issued: 09/09/1980
• Est. Priority Date: 04/20/1977
• Status: Expired due to Term

• Current Assignee: The Garrett Corporation
• Original Assignee: The Garrett Corporation
• Inventors: Corrigan, Charles E.
• Primary Examiner(s): Powell, Jr., Everette A.
• Application Number:
  US05/789,371
• Time in Patent Office: 1,238 Days
• Field of Search: 415/115, 415/116, 416/97, 416/97 A, 416/229 A, 416/231 R, 416/96 A
• US Class Current: 416/97.00A
• CPC Class Codes: F01D 5/147 Construction, i.e. structural features, e.g. of weight-saving hollow blades F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18
• CPC Class Codes: F01D 5/18 Hollow blades, i.e. blades with cooling or heating channels or cavities structure of hollow blades in general F01D5/147; Heating, heat-insulating or cooling means on blades
• CPC Class Codes: F01D 5/34 Rotor-blade aggregates of unitary construction , e.g. formed of sheet laminae; discs formed of sheet laminae F01D5/028; ceramic materials F01D5/284, composite materials F01D5/282
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

Improved structure and method for an internally cooled, laminated stator or turbine blade for turbomachinery includes internal cooling passage configurations within each lamina which promote different forms of cooling of the internal or external surfaces of the blade.

Claims

1. An airfoil for use in turbomachinery comprising a plurality of thin, stacked laminae bonded together to form a major portion of said airfoil and a major portion of an external surface of the airfoil adapted to be arranged in momentum exchange relationship with the major fluid past said airfoil;

each lamina of a set of said laminae having internal recesses therein defining internal cooling passages within said airfoil, and defining upstream and downstream exhaust ports opening onto said external surface at locations spaced chordwise along said external surface, said upstream exhaust port of each lamina configured to extend downstream in a chordwise direction along said external surface a sufficient distance to intercept the associated downstream exhaust port.

2. An airfoil as set forth in claim 1, wherein said airfoil comprises a stator blade.

3. An airfoil as set forth in claim 2, wherein said laminae form major portions of both a pressure external surface and a suction external surface, said upstream and downstream exhaust ports opening onto said pressure external surface.

4. An airfoil as set forth in claim 3, wherein each lamina defines upstream and downstream exhaust ports opening onto both of said external pressure and suction surfaces.

5. An airfoil as set forth in claim 1, wherein said upstream and downstream exhaust ports each curve in a chordwise downstream direction and are arranged whereby the effective angle between exhaust flow therefrom and the direction of said major fluid flow past the airfoil is less than approximately five degrees.

6. An aerodynamic airfoil blade for use in turbomachinery comprising a plurality of stacked laminae bonded together to form said blade with an external surface thereof adapted to be arranged in momentum exchange relationship with the working fluid flow of the turbomachinery;

said laminae having through apertures therein defining internal cooling passages within said blade;

at least some of said laminae having partial recesses therein cooperating with adjacent laminae to define cooling paths within individual laminae;

at least one set of said recesses defining upstream and downstream exhaust ports for the associated lamina opening onto said external surface of the blade at locations spaced chordwise along said external surface for exhausting cooling flow into said working fluid flow;

each of said recesses of said one set arranged whereby the effective angle between exhaust flow from each of said exhaust ports and the direction of said working fluid flow at the associated exhaust port is less than approximately five degrees, said upstream exhaust port of each lamina configured to extend downstream in a chordwise direction along said external surface a sufficient distance to intercept the associated downstream exhaust port.

7. An airfoil blade as set forth in claim 6, wherein said effective angle is approximately three degrees.

8. An airfoil blade as set forth in claim 7, wherein said airfoil blade comprises a stator blade.

9. An airfoil for use in turbomachinery comprising a plurality of thin, stacked laminae bonded together to form a major portion of said airfoil;

each lamina of a set of said laminae having a relatively thin external wall, said external walls of said set together defining a major portion of an external surface of said airfoil adapted to be arranged in momentum exchange relationship with the working fluid flow of said turbomachinery;

each lamina of said set having a relatively large internal through passage, said central passages together defining an internal cavity in said blade adapted to receive cooling fluid flow;

each lamina of said set having an inner wall spaced closely inwardly of said external wall and extending generally parallel thereto to define a through zone therebetween, said through zones together forming an impingement zone between said external and inner walls extending along the length of said major portion of the airfoil external surface;

each lamina of said set having a plurality of recesses in said inner wall extending generally perpendicularly to the inner face of said external wall whereby cooling flow from said cavity passes through said recesses into said impingement zone to impinge substantially perpendicularly upon said inner face to promote cooling of said external wall; and

means defining an exhaust path for exhausting cooling flow from said impingement zone, said external walls of the set defining major portions of both an external suction surface and an external pressure surface of said stator blade, said inner wall being spaced inwardly of the portion of said external defining a major portion of said external suction surface of the stator blade, said means defining an exhaust path including an exhaust port opening onto said external pressure surface of the stator blade.

10. An airfoil as set forth in claim 9, wherein said airfoil comprises a stator blade.

11. An airfoil as set forth in claim 9, wherein said airfoil comprises a cooled, rotary turbine blade for use in turbomachinery.

12. An airfoil as set forth in claim 11, wherein said external walls of the set together define major portions of both an external pressure surface and an external suction surface of said turbine blade, said inner wall being spaced closely inwardly of both said external pressure surface and external suction surface, said means defining an exhaust path including exhaust ports in said external wall opening onto both of said external pressure and suction surfaces.

13. An airfoil as set forth in claim 12, wherein said external wall has an inner face exposed to said impingement zone, said inner face having protrusions thereon generally aligned with said recesses in the inner wall to promote turbulence of cooling fluid flow in said impingement zone.

14. In combination with a plurality of airfoils each as set forth in claim 9, a central hub having internal passages for carrying cooling fluid flow, said plurality of airfoils being secured in regularly spaced relationship about the periphery of said hub and extending radially outwardly therefrom, said internal cavities of each of said airfoils communicating with said internal passages of said central hub.

15. A cooled, nonrotating stator blade for use in turbomachinery comprising a plurality of thin, stacked laminae bonded together to form the major portion of said stator blade including external pressure and suction surfaces thereof adapted to be arranged in momentum exchange relationship with fluid flow of the turbomachinery, each lamina comprising:

a single peripheral wall forming segments of said external pressure and suction surfaces and surrounding a relatively large central cavity for receiving cooling fluid flow;

a plurality of struts extending span-wise across said central cavity and with opposite ends integrally formed with said peripheral wall, the thickness of said struts being less than that of said peripheral wall;

a plurality of separate recesses in said peripheral wall extending from said central cavity to open onto said pressure and suction surfaces, each of said recesses comprising;

a pair of span-wise extending parallel legs opening separately into said central cavity,

a chordwise extending bight communicating with obth of said legs, and

a single exhaust port section extending from approximately the center of said bight outwardly to open onto the associated segment of the external surface, said exhaust port section curving in a chordwise downstream direction and arranged whereby the effective angle between exhaust flow from said exhaust port section and the direction of said fluid flow of the turbomachinery is less than approximately five degrees, said exhaust port section extending along said associated segment of the external surface a sufficient distance to intercept the exhaust port section of the downstream next-adjacent recess.

16. A cooled, nonrotating stator blade for use in turbomachinery comprising a plurality of thin laminae stacked generally in a first direction and bonded together to form the major portion of said stator blade including external pressure and suction surfaces thereof adapted to be arranged in momentum exchange relationship with fluid flow of the turbomachinery, each lamina comprising:

a peripheral wall including pressure and suction sections respectively forming segments of said external pressure and suction surfaces, said wall surrounding a relatively large central cavity for receiving cooling fluid flow;

an inner wall spaced closely inwardly of said suction section of the peripheral wall and extending generally parallel thereto to define an impingement zone of said central cavity extending along the length of said suction section of the peripheral wall;

a first set of struts extending generally spanwise across said central cavity between said pressure and suction sections of the peripheral wall to divide said central cavity into separate compartments, said inner wall, peripheral wall and first set of struts being of equal thickness in said first direction;

a second set of struts having a thickness less than that of said peripheral wall and arranged to extend generally spanwise across said compartments;

a plurality of recesses in said inner wall extending generally peripendicularly thereto whereby cooling flow from said cavity passes through said recesses into said impingement zone to impinge substantially perpendicularly upon an inner face of said suction section of the peripheral wall to promote cooling of said suction section without introducing cooling flow onto said external suction surface; and

exhaust duct recesses in at least some of said first set of struts opening into said impingement zone and opening onto said external pressure surface for exhausting cooling fluid flow from said impingement zone, said exhaust ducts curving in a chordwise downstream direction and arranged whereby the effective angle between exhausting cooling flow from said exhaust duct and the direction of said fluid flow of the turbomachinery is less than approximately five degrees, said exhaust duct extending along said segment of the external pressure surface a sufficient distance to intercept the exhaust duct of the downstream next-adjacent strut of said first set.