BACKGROUND

Instrumented flow path hardware for aerodynamic test engines typically include vanes or blades with trenches machined into airfoil surfaces for the routing of small diameter tubing for the transmission of static pressure from sensor to transducer.

Hardware is typically fabricated from high strength metallic materials to accommodate the geometric complexity of the trenching and the increased stresses due to removal of material. The design and fabrication of test hardware requires substantial resources in terms of manpower, schedule and cost.

In addition, the presence of small diameter tubing on the surfaces of airfoils and in the flow path alters the flow of air and affects the actual pressure being measured.

SUMMARY

A static pressure device including a hypotube lattice is incorporated into gas turbine engine components such as airfoils to measure surface pressure on the airfoils. A lattice is formed from a plurality of hypotubes aligned in a first direction and held in place with a plurality of reinforcing wires that are aligned essentially perpendicular to the hypotubes.

The lattice is embedded internally between layers of a laminate composite component such as an airfoil such that the first direction above is the radial direction of the airfoil. The airfoil pressure side or suction side or both may have a plurality of bundles of the lattice static pressure device.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is a perspective view of a hypotube lattice.

FIG. 2 is a perspective view of the hypotube lattice of FIG. 1 embedded in an airfoil.

FIG. 3 is a section view of the airfoil of FIG. 2 taken along the line 3-3 of FIG.

2.

FIG. 4 is an enlarged view of a portion of the section view of FIG. 3.

FIG. 5 is an enlarged view of the lower end of the lattice of FIG. 2 FIG. 6 is a further enlarged view of the lattice of FIG. 5.

DETAILED DESCRIPTION

The term "hypotube" is standard in industry and describes hollow metal tubes of very small diameter. Hypotubes are used in the medical industry and are produced primarily from 304 and 304L (low-carbon) welded stainless steel. 304 stainless steel has relatively low carbon content (0.08 percent maximum) and resists corrosion better than 302 stainless steel. Three different means for welding the tubes are used in the industry. Gas tungsten arc welding (GTAW) is the oldest method and is still widely used. Plasma welding is a variation on GTAW, and laser welding is the newest method. All are effective. Typical hypotubes have an outer diameter of about 0.032 inches (0.3 to about 0.4 mm). Wall thicknesses are about 0.375 mm.

The hypotubes and wire lattice brazement or weldment 11 in FIG. 1 is formed from small diameter hypotubes 13 with crosswise reinforcing wires 15. Five bundles 16A- 16E each contain five hypotubes 13 of different lengths. Inlet ends + from each bundle 16A- 16E are located at a plurality of locations to provide a array of opening locations. FIG. 1 shows each of the five hypotubes with a length corresponding to a hypotube in all five bundles 16A-16E to present five axial or chord directed lines of openings +. The invention as depicted has 5 chordwise and 5 spanwise pressure sensing locations but the number of locations could be increased or decreased in either direction as required.

Lattice 11 in FIG. 1 is laid-up in composite laminate airfoil 17 of FIG. 2. The tubes are typically sealed to prevent the intrusion of resin during the molding process. In FIG. 2, airfoil 17 is one of two vanes extending between base exit wall 18 A and top endwalll8B. Airfoil 17 includes pressure surface 19 and suction surface 20, which extent in a chord wise (or axial) direction from leadingedgel7L to trailing edge 17T and extend in a span wise (or radial) direction from base end wall 18 A to tip end wall 18B. Inlet ends of hypotubes 13, shown by the +, take in pressure on pressure surface 19 of airfoil 17 and to exit ends at platforml7A of airfoil 17 shown by the arrows. In FIG. 2, inlet ends + provide pressure to hypotubes 13. FIG. 2 illustrates an airfoil in the form of a vane, but blades and other gas turbine engine components exposed to fluid pressure are equally suitable for the present invention. The invention may also apply to single vanes or blades or components having multiple vanes or blades connected together as a single component.

Drilling into the face of vane 17 connects the individual hypotubes 13 at inlets + to the flowfield to allow measurement of the fluid pressure field at various locations on pressure surface 19 of airfoil 17 at the bottom 17A of airfoil 17 in FIG. 3. Bundles 23A-23E of five hypotubes each is installed in the vane pressure side laminate 19. Airfoils have a pressure side 19 and a suction side 20. Radiography or witness marks of tubes 13 in the surface of the laminate show locations of tubes for drilling to openings+. FIG. 4 is an enlarged view of a portion of pressure side 19 of vane 17. A bundle 23a of hypotubes 13 are held in vane 17 between plies 51, 53, 55, 57, 59 and 61, with ply 57 being shown as segmented at 57a and 57b if the plies are small and close together. Otherwise no segmenting is necessary. Plies have been depicted as 0.012 inches ( 0.1mm) thick, but the invention can accommodate a wide array of ply thicknesses. Bundle 23a contains five hypotubes identified above. It has been found to be effective in evaluating the pressure on surface 19 of vane 17 to provide a plurality of bundles 23a-e as in FIG. 3.

The five bundles 23 extend out end 17a of vane 17 in FIG. 5 and FIG. 6 and are connected to additional lengths of tubing that ultimately connect to electrical pressure transducers, of conventional design, not shown, where DC voltage is proportional to static pressure in tubes 13.

While the invention has been described with reference to an exemplary embodiment(s), it will be understood by those skilled in the art that various changes may be made and equivalents may be substituted for elements thereof without departing from the scope of the invention. In addition, many modifications may be made to adapt a particular situation or material to the teachings of the invention without departing from the essential scope thereof. Therefore, it is intended that the invention not be limited to the particular embodiment(s) disclosed, but that the invention will include all embodiments falling within the scope of the appended claims.