Engine component test apparatus

• US 5,178,003 A
• Filed: 07/31/1991
• Issued: 01/12/1993
• Est. Priority Date: 10/24/1990
• Status: Expired due to Fees

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Wesorick, Richard S.
• Primary Examiner(s): RAEVIS, ROBERT R
• Application Number:
  US07/738,384
• Time in Patent Office: 531 Days
• Field of Search: 73/168, 73/118.1, 415/118
• US Class Current: 73/112.01
• CPC Class Codes: G01L 3/247 by measuring and simultaneously multiplying tractive or propulsive force and velocity
• CPC Class Codes: G01L 3/26 Devices for measuring efficiency, i.e. the ratio of power output to power input

Abstract

A component test apparatus is provided for measuring the torque of an aircraft engine inducer nozzle to characterize the efficiency of the nozzle prior to engine launch. A frictionless mount rotatably supports a forward inner nozzle support which combines with the support to form a pressurizable plenum for communicatively discharging air through the nozzle and imparting annular motion to the apparatus characteristic of the efficiency of the nozzle.

Claims

1. A component test apparatus for evaluating airflow efficiency in a vaned inducer nozzle comprising:

(a) sealing means for supporting a forward inner nozzle support including an inducer nozzle and forming a first plenum with said forward inner nozzle support, said first plenum having a primary axis;

(b) means for supplying pressurized air to said first plenum;

(c) an exterior support structure partially surrounding said first plenum;

(d) a frictionless support means for demountably supporting said first plenum for substantially frictionless rotation relative to said exterior support structure in a first direction and only in a first plane substantially perpendicular to said primary axis in response to an airflow through said nozzle; and

(e) measuring means attached to said first plenum and to said exterior support for measuring a force produced by rotation of said first plenum in response to said applied airflow exiting said vaned inducer nozzle wherein said force is linearly related to airflow.

2. The component test apparatus of claim 1 wherein said test apparatus includes a forward inner nozzle support comprising an annular channel having an inducer nozzle projecting from a first side thereof.

3. The component test apparatus of claim 2 wherein said inducer nozzle includes a plurality of vanes fixedly mounted in said inducer nozzle for imparting a swirl to an airflow through said inducer nozzle.

4. The component test apparatus of claim 2 wherein said inducer nozzle is circumferential.

5. The component test apparatus of claim 2 wherein:

(a) said forward inner nozzle support includes

(i) a forward flange mount

(ii) an aft flange mount

(b) said sealing means comprises;

(i) a forward inner nozzle support adaptor plate

(ii) an annular-shaped, open faced mounting bracket having a first face for sealingly receiving said forward inner nozzle support aft flange mount;

(iii) a forward inner nozzle support blank-off plate for sealingly receiving said forward inner nozzle support forward flange mount;

(iv) an air deflector; and

(c) said forward inner nozzle support, said forward inner nozzle support adaptor plate, said annular shaped, open-faced mounting bracket, said forward inner nozzle support blank-off plate and said air deflector form a sealed chamber vented through said vaned inducer nozzle.

6. The component test apparatus of claim 5 wherein said an annular-shaped, open faced mounting bracket includes an adaptor plate for receiving said aft flange mount.

7. The component test apparatus of claim 5 wherein:

(a) said forward inner nozzle support vaned inducer nozzle includes a first surface for positioning adjacent an inner flowpath of an aircraft engine;

(b) said annular shaped, open faced mounting bracket includes an interior surface; and

(c) said inducer nozzle first surface is positioned adjacent said interior surface of said annular shaped, open-faced mounting bracket.

8. The component test apparatus of claim 5 wherein said sealing means includes a hollow shaft fixedly attached to said annular-shaped, open faced bracket and mounted in said frictionless support comprising a circumferential air bearing, said hollow shaft being adapted for connection to a pressurized air supply plenum for pressurizing said first plenum and forward inner nozzle support.

9. The component test apparatus of claim 8 wherein said air bearing opposes axial movement of said shaft.

10. The component test apparatus of claim 1 wherein said sealing means comprises a circumferential 360°

annular bracket.

11. The component test apparatus of claim 1 wherein said frictionless support means comprises an air bearing defining a guide for receiving a hollow shaft in rotational relationship therein.

12. The component test apparatus of claim 11 wherein said means for supplying pressurized air to said first plenum comprises a rotatable hollow shaft extending between a said first plenum and a supply of pressurized air.

13. The component test apparatus of claim 12 wherein said frictionless support means includes a face and said hollow shaft includes a substantially planar end face abutting said frictionless support means face.

14. The component test apparatus of claim 12 wherein said hollow shaft defines an air passageway for supplying pressurized air to said first plenum and said forward inner nozzle support and includes a flow meter for measuring air flow therethrough.

15. The component test apparatus of claim 1 wherein said means for measuring force comprises a load cell system.

16. A component test apparatus for evaluating airflow efficiency in an inducer nozzle comprising:

(a) means for demountably supporting a forward inner nozzle support, including an inducer nozzle, for substantially planar frictionless rotation in response to an airflow through said inducer nozzle;

(b) means coupled to said forward inner nozzle support for supplying air thereto and producing a torque which rotates said inducer nozzle about a fixed axis; and

(c) means for measuring said torque for the purpose of determining the efficiency of said inducer nozzle.