Temperature measurement in turbine engines

• US 4,934,137 A
• Filed: 12/14/1988
• Issued: 06/19/1990
• Est. Priority Date: 12/14/1988
• Status: Expired due to Fees

• Current Assignee: Alliedsignal Inc.
• Original Assignee: Alliedsignal Inc.
• Inventors: MacKay, Charles G.
• Primary Examiner(s): Casaregola, Louis J.
• Application Number:
  US07/284,214
• Time in Patent Office: 552 Days
• Field of Search: 60/39.33, 60/39.83, 415/118, 356/43, 356/44, 374/121, 374/125, 374/132
• US Class Current: 60/803
• CPC Class Codes: F01D 17/085 to temperature
• CPC Class Codes: F01D 21/003 Arrangements for testing or measuring for measuring vibrations G01H

Abstract

A turbine engine (10) having an optical pyrometer (38) for temperature measurement within the turbine (24) is disclosed. The shroud (64) of the turbine has a deflection surface (142) on the downstream side of an aperture (60) through which the pyrometer (38) images an area (56) in the turbine. The deflection surface (142) deflects into the flow path (26) of the combustion gas particulates which would otherwise enter a plenum (134). The imaging probe (52) of the pyrometer (38) is surrounded by a plenum (134) along its axial length to provide an air purging arrangement for the plenum (134) and the lens (66). Various geometrical relationships between the probe (52) and the shroud (64), and between the probe and the inner surface (98,136) of the plenum (134) are employed to minimize entry of particulates into the plenum and to provide an aerodynamically efficient purging system. Air tapped from a compressor (12) is used to cool the pyrometer (38) and supply the plenum (134).

Claims

1. A turbine engine having a compressor adapted to compress air inducted into said engine, a combustor adapted to burn a mixture of fuel and compressed air to produce combustion gas, a turbine adapted to produce rotary motion in response to pressure exerted by said combustion gas as it moves downstream along a flow path defined in part by a radially inward-facing surface of a turbine shroud, said turbine being drivingly engaged via a shaft with said compressor to impart said rotary motion thereto, and apparatus for monitoring temperature in said turbine, wherein said apparatus comprises:

a generally cylindrical imaging probe defining a radiation path extending axially therethrough, said probe having at one end a lens defining a forward focus, said lens having a convex outer surface, said outer surface facing and being spaced from an aperture formed in said turbine shroud so that said forward focus is positioned approximately at said aperture, said probe being secured and positioned in said engine to image an area of a component of said turbine through said aperture;

a radiation detector for producing electrical indications of the intensity of infrared radiation traversing said radiation path, said detector being positioned with respect to said radiation path such that an image of said area is formed thereon; and

means for defining a plenum surrounding at least an axially extending portion of said probe including said lens, said plenum extending in a downstream direction from an inlet thereto to said aperture, wherein said inlet is positioned upstream from said lens so that air entering said plenum via said inlet is constrained to flow along said axially extending portion, past said lens, and through said aperture.

2. A turbine engine as in claim 1 wherein said turbine shroud is beveled or rounded along a downstream portion of a rim surrounding said aperture to provide a deflection surface whereby particulates which would otherwise migrate into said plenum or be propelled therein by said combustion gas are deflected back into said flow path.

3. A turbine engine as in claim 2 wherein said defining means has an inner surface defining first and second portions thereof, said defining means having larger and smaller inside diameters over said first and second portions, respectively, said larger-diameter portion being upstream from said outer surface of said lens, said smaller-diameter portion being downstream from said outer surface, said inner surface converging at an angle from said larger-diameter portion to said smaller-diameter portion to form a flow ramp, said flow ramp cooperating with said outer surface to define a gap distance therebetween.

4. A turbine engine as in claim 3 wherein said probe has a cylindrical exterior surface over said axially extending portion, said cylindrical surface defining a diameter that is less than twenty-four times said gap distance.

5. A turbine engine as in claim 4 wherein said probe has a curved exterior surface between said cylindrical surface and said one end, and said curved exterior surface converging, in a radially inward direction in relation to said probe, from said cylindrical surface to said one end.

6. A turbine engine as in claim 5 wherein the radius of curvature of said curved exterior surface is at least one-tenth said gap distance.

7. A turbine engine having a compressor adapted to compress air inducted into said engine, a combustor adapted to burn a mixture of fuel and compressed air to produce combustion gas, a turbine adapted to produce rotary motion in response to pressure exerted by said combustion gas as it moves downstream along a flow path defined in part by a radially inward-facing surface of a turbine shroud, said turbine being drivingly engaged via a shaft with said compressor to impart said rotary motion thereto, and apparatus for monitoring temperature in said turbine, wherein said apparatus comprises:

a generally cylindrical imaging probe defining a radiation path extending axially therethrough, said probe having at one end a lens defining a forward focus, said lens having a convex outer surface, said outer surface facing and being spaced from an aperture formed in said turbine shroud so that said forward focus is positioned approximately at said aperture, said probe being secured and positioned in said engine to image an area of a component of said turbine through said aperture, said aperture being surrounded by a rim which is beveled or rounded along a downstream portion thereof to provide a deflection surface whereby particulates which would otherwise migrate into said plenum or be propelled therein by said combustion gas are deflected back into said flow path;

a radiation detector for producing electrical indications of the intensity of infrared radiation traversing said radiation path, said detector being positioned with respect to said radiation path such that an image of said area is formed thereon; and

means for defining a plenum surrounding at least an axially extending portion of said probe including said lens, said plenum extending in a downstream direction from an inlet thereto to said aperture, wherein said inlet is positioned upstream from said lens so that air entering said plenum via said inlet is constrained to flow along said axially extending portion, past said lens, and through said aperture, said defining means having an inner surface defining first and second portions thereof, said defining means having larger and smaller inside diameters over said first and second portions, respectively, said larger-diameter portion being upstream from said outer surface of said lens, said smaller-diameter portion being downstream from said outer surface, said inner surface converging at an angle from said larger-diameter portion to said smaller-diameter portion to form a flow ramp, said flow ramp cooperating with said outer surface to define a gap distance therebetween, said flow ramp being substantially parallel to said outer surface.

8. A turbine engine having a compressor adapted to compress air inducted into said engine, a combustor adapted to burn a mixture of fuel and compressed air to produce combustion gas, a turbine adapted to produce rotary motion in response to pressure exerted by said combustion gas as it moves downstream along a flow path defined in part by a radially inward-facing surface of a turbine shroud, said turbine being drivingly engaged via a shaft with said compressor to impart said rotary motion thereto, and apparatus for monitoring temperature in said turbine, wherein said apparatus comprises:

a generally cylindrical imaging probe defining a radiation path extending axially therethrough, said probe having at one end a lens defining a forward focus, said lens having a convex outer surface, said outer surface facing and being spaced from an aperture formed in said turbine shroud so that said forward focus is positioned approximately at said aperture, said probe being secured and positioned in said engine to image an area of a component of said turbine through said aperture, said aperture being surrounded by a rim which is beveled or rounded along a downstream portion thereof to provide a deflection surface whereby particulates which would otherwise migrate into said plenum or be propelled therein by said combustion gas are deflected back into said flow path;

a radiation detector for producing electrical indications of the intensity of infrared radiation traversing said radiation path, said detector being positioned with respect to said radiation path such that an image of said area is formed thereon; and

means for defining a plenum surrounding at least an axially extending portion of said probe including said lens, said plenum extending in a downstream direction from an inlet thereto to said aperture, wherein said inlet is positioned upstream from said lens so that air entering said plenum via said inlet is constrained to flow along said axially extending portion, past said lens, and through said aperture, said defining means having an inner surface defining first and second portions thereof, said defining means having larger and smaller inside diameters over said first and second portions, respectively, said larger-diameter portion being upstream from said outer surface of said lens, said smaller-diameter portion being downstream from said outer surface, said inner surface converging at an angle from said larger-diameter portion to said smaller-diameter portion to form a flow ramp, said flow ramp cooperating with said outer surface to define a gap distance therebetween, said flow ramp being substantially parallel to said outer surface of said lens, said probe having a cylindrical exterior surface over said axially extending portion, said cylindrical surface defining a diameter that is less than twenty-four times said gap distance, said probe having a curved exterior surface between said cylindrical surface and said one end, said curved exterior surface converging in a radially inward direction in relation to said probe from said cylindrical surface to said one end, said curved exterior surface having a radius of curvature that is at least one-tenth said gap distance.

9. A turbine engine as in claim 8 further comprising means, secured to or integral with said probe, being surrounded by said defining means, and being positioned downstream from said inlet and immediately upstream from said axially extending portion of said probe, for redirecting air flowing along said plenum to produce a spiral flow thereof.

10. A turbine engine as in claim 9 wherein said redirecting means defines an alternating series of merlons and crenels extending circumferentially around said probe, said merlons abutting said inner surface of said defining means and said crenels being angled in relation to the longitudinal axis of said probe.

11. A turbine engine as in claim 10 wherein the angle of said crenels with respect to said axis of said probe is in the range of from five to thirty degrees.

12. A turbine engine having a compressor adapted to compress air inducted into said engine, a combustor adapted to burn a mixture of fuel and compressed air to produce combustion gas, a turbine adapted to produce rotary motion in response to pressure exerted by said combustion gas as it moves downstream along a flow path defined in part by a radially inward-facing surface of a turbine shroud, said turbine being drivingly engaged via a shaft with said compressor to impart said rotary motion thereto, and apparatus for monitoring temperature in said turbine, wherein said apparatus comprises:

a generally cylindrical imaging probe defining a radiation path extending axially therethrough, said probe having at one end a lens defining a forward focus, said lens having a convex outer surface, said outer surface facing and being spaced from an aperture formed in said turbine shroud so that said forward focus is positioned approximately at said aperture, said probe being secured and positioned in said engine to image an area of a component of said turbine through said aperture;

a radiation detector positioned within said probe for producing electrical indications of the intensity of infrared radiation traversing said radiation path, said detector being positioned with respect to said radiation path such that an image of said area is formed thereon; and

means for defining a plenum surrounding at least an axially extending portion of said probe including said lens, said plenum extending in a downstream direction from an inlet thereto to said aperture, wherein said inlet is positioned upstream from said lens so that air entering said plenum via said inlet is constrained to flow along said axially extending portion, past said lens, and through said aperture, said inlet being positioned to direct air onto said probe at an axial position thereof which nominally corresponds to that of said detector.

13. A turbine engine as in claim 12 wherein said turbine shroud is beveled or rounded along a downstream portion of a rim surrounding said aperture to provide a deflection surface, whereby particulates which would otherwise migrate into said plenum or be propelled therein by said combustion gas are deflected back into said flow path.

14. A turbine engine as in claim 13 wherein said axially extending portion of said probe has a cylindrical exterior surface, and a curved exterior surface between said cylindrical surface and said outer surface of said lens, and wherein said curved exterior surface converges in a radially inward direction from said cylindrical surface to said outer surface.

15. A turbine engine as in claim 14 wherein said defining means has an inner surface defining first and second axially extending portions thereof, said defining means having larger and smaller inside diameters over said first and second portions, respectively, said larger-diameter portion being generally upstream from said outer surface of said lens and said smaller-diameter portion being generally downstream from said outer surface, said inner surface converging from said larger-diameter portion to said smaller-diameter portion to form a flow ramp, said flow ramp cooperating with said outer surface to define a gap distance therebetween.

16. A turbine engine as in claim 15 wherein said cylindrical surface defines an outside diameter of said probe and said outside diameter is less than twenty-four times said gap distance.

17. A turbine engine as in claim 16 wherein said flow ramp is substantially parallel to said outer surface of said lens.

18. A turbine engine having a compressor adapted to compress air inducted into said engine, a combustor adapted to burn a mixture of fuel and compressed air to produce combustion gas, a turbine adapted to produce rotary motion in response to pressure exerted by said combustion gas as it moves downstream along a flow path defined in part by a radially inward-facing surface of a turbine shroud, said radially inward-facing surface defining a sight aperture and a rim surrounding said sight aperture, said turbine being drivingly engaged with said compressor to impart said rotary motion thereto, and apparatus for monitoring temperature in said turbine, wherein said apparatus comprises:

an imaging probe defining a radiation path extending axially therethrough, said probe having an axially extending exterior surface leading to a forward end of said probe, said forward end having a lens with a convex outer surface, said outer surface facing said sight aperture whereby said probe images an area of a component of said turbine through said sight aperture, said lens defining a forward focus and being spaced from said sight aperture whereby said focus is positioned approximately at said aperture;

a radiation detector for producing electrical signals indicative of the intensity of infrared radiation traversing said radiation path, said detector being positioned in relation to said radiation path whereby an image of said area is formed on said detector; and

means for defining a plenum between said lens and said sight aperture and an inlet to said plenum whereby air which enters said plenum through said inlet is constrained to flow along said plenum and through said sight aperture.

19. A turbine engine as in claim 18 wherein said plenum defining means surrounds at least a portion of said axially extending surface of said probe and wherein said inlet is positioned such that air entering said plenum therefrom is constrained to flow along said portion, past said lens, and through said sight aperture.

20. A turbine engine as in claim 19 wherein said plenum defining means has an inner surface defining first and second portions thereof, said defining means having larger and smaller inside diameters over said first and second portions, respectively, said larger-diameter portion being generally upstream from said outer surface of said lens and said smaller-diameter portion being generally downstream from said outer surface, said inner surface converging from said larger-diameter portion to said smaller-diameter portion to form a flow ramp, said flow ramp cooperating with said outer surface to define a gap distance therebetween.

21. A turbine engine as in claim 20 wherein said portion of said exterior surface of said probe has a cylindrical surface defining an outside diameter, the ratio of said outside diameter to said gap distance being less than twenty-four.

22. A turbine engine as in claim 21 wherein said portion of said exterior surface of said probe has a curved surface positioned between said cylindrical surface and said outer surface of said lens, said curved surface converging in a radially inward direction from said cylindrical surface to said outer surface.

23. A turbine engine as in claim 18 wherein said lens defines a forward focus and said probe is positioned in relation to said sight aperture such that said forward focus has substantially the same position along an axis defined by said probe as does said sight aperture.

24. A turbine engine having a compressor adapted to compress air inducted into said engine, a combustor adapted to burn a mixture of fuel and compressed air to produce combustion gas, a turbine adapted to produce rotary motion in response to pressure exerted by said combustion gas as it moves downstream along a flow path defined in part by a radially inward-facing surface of a turbine shroud, said radially inward-facing surface defining a sight aperture, said turbine being drivingly engaged with said compressor to impart said rotary motion thereto, and apparatus for monitoring temperature in said turbine, wherein said apparatus comprises:

an imaging probe defining a radiation path extending axially therethrough, said probe having an axially extending exterior surface leading to a forward end of said probe, said forward end having a lens with a convex outer surface, said outer surface facing said sight aperture whereby said probe images an area of a component of said turbine through said sight aperture;

a radiation detector for producing electrical signals indicative of the intensity of infrared radiation traversing said radiation path, said detector being positioned in relation to said radiation path whereby an image of said area is formed on said detector; and

means for defining a plenum between said lens and said sight aperture and an inlet to said plenum whereby air which enters said plenum through said inlet is constrained to flow along said plenum and through said sight aperture, said plenum-defining means surrounding at least an axially extending portion of said axially extending surface of said probe, said inlet being positioned such that air entering said plenum therefrom is constrained to flow along said axially extending portion, past said lens, and through said sight aperture, said plenum-defining means having an inner surface defining first and second portions thereof, said defining means having larger and smaller inside diameters over said first and second portions, respectively, said larger-diameter portion being generally upstream from said outer surface of said lens and said smaller-diameter portion being generally downstream from said outer surface, said inner surface converging from said larger-diameter portion to said smaller-diameter portion to form a flow ramp, said flow ramp cooperating with said outer surface to define a gap distance therebetween, said flow ramp being substantially parallel to said outer surface.

25. A turbine engine having a compressor adapted to compress air inducted into said engine, a combustor adapted to burn a mixture of fuel and compressed air to produce combustion gas, a turbine adapted to produce rotary motion in response to pressure exerted by said combustion gas as it moves downstream along a flow path defined in part by a radially inward-facing surface of a turbine shroud, said radially inward-facing surface defining a sight aperture, said turbine being drivingly engaged with said compressor to impart said rotary motion thereto, and apparatus for monitoring temperature in said turbine, wherein said apparatus comprises:

an imaging probe defining a radiation path extending axially therethrough, said probe having an axially extending exterior surface leading to a forward end of said probe, said forward end having a lens with a convex outer surface, said outer surface facing said sight aperture whereby said probe images an area of a component of said turbine through said sight aperture;

a radiation detector for producing electrical signals indicative of the intensity of infrared radiation traversing said radiation path, said detector being positioned in relation to said radiation path whereby an image of said area is formed on said detector; and

means for defining a plenum between said lens and said sight aperture and an inlet to said plenum, said plenum-defining means surrounding at least an axially extending portion of said axially extending surface of said probe, said inlet being positioned such that air entering said plenum therefrom is constrained to flow along said axially extending portion, past said lens, and through said sight aperture, said plenum-defining means having an inner surface defining first and second portions thereof, said defining means having larger and smaller inside diameters over said first and second portions, respectively, said larger-diameter portion being generally upstream from said outer surface of said lens and said smaller-diameter portion being generally downstream from said outer surface, said inner surface converging from said larger-diameter portion to said smaller-diameter portion to form a flow ramp, said flow ramp cooperating with said outer surface to define a gap distance therebetween, said probe cooperating with said larger-diameter portion of said inner surface and with said flow ramp to define first and second cross-sectional areas respectively, of said plenum, the ratio of said second cross-sectional area to said first cross-sectional area being within a range of from 0.028 times "X" to 0.040 times "X";

where "X" equals ninety minus a surface angle of said outer surface, said surface angle being determined where said outer surface is closest to said flow ramp.

26. A turbine engine having a compressor adapted to compress air inducted into said engine, a combustor adapted to burn a mixture of fuel and compressed air to produce combustion gas, a turbine adapted to produce rotary motion in response to pressure exerted by said combustion gas as it moves downstream along a flow path defined in part by a radially inward-facing surface of a turbine shroud, said radially inward-facing surface defining a sight aperture, said turbine being drivingly engaged with said compressor to impart said rotary motion thereto, and apparatus for monitoring temperature in said turbine, wherein said apparatus comprises:

an imaging probe defining a radiation path extending axially therethrough, said probe having an axially extending exterior surface leading to a forward end of said probe, said forward end having a lens with a convex outer surface, said outer surface facing said sight aperture whereby said probe images an area of a component of said turbine through said sight aperture, said lens defining a forward focus and said probe being positioned in relation to said sight aperture such that said forward focus has substantially the same position along an axis defined by said probe as does said sight aperture, said exterior surface of said probe having a portion near said lens that converges in a radially inward direction so that said outer surface and said portion form a substantially continuous surface;

a radiation detector for producing electrical signals indicative of the intensity of infrared radiation traversing said radiation path, said detector being positioned in relation to said radiation path whereby an image of said area is formed on said detector; and

means for defining a plenum between said lens and said sight aperture and an inlet to said plenum whereby air which enters said plenum through said inlet is constrained to flow along said plenum and through said sight aperture.

27. A turbine engine having a compressor adapted to compress air inducted into said engine, a combustor adapted to burn a mixture of fuel and compressed air to produce combustion gas, a turbine adapted to produce rotary motion in response to pressure exerted by said combustion gas as it moves downstream along a flow path defined in part by a radially inward-facing surface of a turbine shroud, said radially inward-facing surface defining a sight aperture, said turbine being drivingly engaged with said compressor to impart said rotary motion thereto, and apparatus for monitoring temperature in said turbine, wherein said apparatus comprises:

an imaging probe defining a radiation path extending axially therethrough, said probe having an axially extending exterior surface leading to a forward end of said probe, said forward end having a lens with a convex outer surface, said outer surface facing said sight aperture whereby said probe images an area of a component of said turbine through said sight aperture;

a radiation detector for producing electrical signals indicative of the intensity of infrared radiation traversing said radiation path, said detector being positioned in relation to said radiation path whereby an image of said area is formed on said detector; and

means for defining a plenum between said lens and said sight aperture and an inlet to said plenum, said plenum-defining means surrounding at least an axially extending portion of said axially extending surface of said probe, said inlet being positioned such that air entering said plenum therefrom is constrained to flow along said axially extending portion, past said lens, and through said sight aperture, said detector being positioned within said probe and said inlet being positioned such that air passing through said inlet into said plenum is directed onto said probe at an axial position thereof which nominally corresponds to that of said detector.