Engine condition calculating device

• US 4,037,782 A
• Filed: 07/12/1976
• Issued: 07/26/1977
• Est. Priority Date: 07/12/1976
• Status: Expired due to Term

• Current Assignee: United States Of America As Represented By The Secretary Of The Army (Government of the United States of America)
• Original Assignee: The United States Of America As Represented By The Secretary Of The Army
• Inventors: Jackson, William Nelson
• Primary Examiner(s): Tomsky, Stephen J.
• Application Number:
  US05/704,712
• Time in Patent Office: 379 Days
• Field of Search: 235/84, 235/88, 235/78 N, 235/78 R, 235/70 A
• US Class Current: 235/84
• CPC Class Codes: G06G 1/0005 characterised by a specific application

Abstract

Daily engine checks or health tests are being developed for determining theondition of an engine by relating significant performance parameters. One such health test, termed "HIT," utilizes exhaust gas temperature along with compressor speed. Since results of this test vary with outside air temperature conversions must be made by maintenance personnel and pilots. A calculating device is provided for this use.

Claims

1. A calculating device for monitoring a turbine engine'"'"'s condition on a daily basis from engine performance parameters N₁, EGT and OAT,

wherein N₁ measures the revolutions per minute of the gas producer section of the engine and is expressed in percent rpm,

wherein EGT is engine gas temperature,

and wherein OAT is outside air temperature, the calculating device comprising

a base plate having

an OAT scale increasing linearly in a predetermined direction and calibrated in degrees Celsius,

an N₁ scale increasing linearly in the same predetermined direction and also calibrated in degrees Celsius, first and second EGT scales in parallel disposition in increasing units, the OAT, N₁ and EGT values being oriented with respect to each other so that for each value of OAT corresponding values of N₁ and EGT are equally spaced on said base plate,

a first overlay plate adapted to overlie the base plate the first overlay having windows over the OAT, N₁ and the first EGT scales, oriented to expose an EGT value on the EGT scale and corresponding values of N₁ and OAT on the other two scales when the plate is moved from one value to another, and having a correction factor scale of numerals imprinted thereon,

and a second overlay plate adapted to overlie the first overlay plate

the second overlay having a window which exposes EGT values on the second EGT scale,

and an indexing line adapted to lie opposite numerals on the correction factor scale to linearly offset the window to a different EGT value on the second EGT scale based on the correction factor.

2. A calculating device for monitoring a turbine engine'"'"'s condition on a daily basis from engine performance parameters N₁, EGT and OAT,

wherein N₁ measures the revolutions per minute of the gas producer section of the engine and is expressed in percent rpm,

wherein EGT is engine gas temperature,

and wherein OAT is outside air temperature, the calculating device comprising

a base plate having OAT, N₁, and a pair of EGT scales imprinted thereon,

the OAT scale being in the range of -50°

C. to +50°

C.,

the N₁ scale being in the range of 73% to 96% and the EGT scales being in the range of 300°

C. to 749°

C.,

the individual OAT, N₁, and EGT values being oriented with respect to each other so that for each value of OAT corresponding values of N₁ and EGT are equally spaced on said base plate,

the equations of correspondence being ##EQU2## wherein OAT, N₁ and EGT are actual or indicated conditions, and OAT_SD, N_1SD and EGT_SD are standard day conditions,

a first overlay plate pivotally attached to overlie the base plate

the first overlay having windows over the OAT, N₁ and one of the EGT scales oriented to expose an EGT value on the EGT scale and corresponding values of N₁ and OAT on the other two scales when the plate is rotated from one value to another,

and having a correction factor scale of numerals imprinted thereon,

and a second overlay plate pivotally attached to overlie the first overlay plate

the second overlay having a window which exposes EGT values on the second EGT scale,

and an indexing line adapted to lie opposite numerals on the correction factor scale to linearly offset the window to a baseline EGT value on the second EGT scale based on the correction factor.

3. The calculating device of claim 2 wherein the N₁ range is 73 to 89 and the EGT range is 325 to 594.

4. The calculating device of claim 2 wherein the N₁ range is 79 to 96 and the EGT range is 325 to 594.

5. The calculating device of claim 2 wherein the N₁ range is 73 to 89 and the EGT range is 361 to 647.

6. The calculating device of claim 2 wherein the N₁ range is 80 to 97 and the EGT range is 432 to 749.

7. The calculating device of claim 2 wherein the window on the second overlay is provided with indicia at 20°

and 30°

variance points warning or grounding the aircraft.