Inlet performance measurement system for gas turbine engine

Patent metadata

Field	Value
Publication number	US-10598041-B2
Application number	US-201715789153-A
Country	US
Kind code	B2
Filing date	Oct 20, 2017
Priority date	Oct 20, 2017
Publication date	Mar 24, 2020
Grant date	Mar 24, 2020

Abstract

A performance measurement system of an inlet of a gas turbine engine includes a probe strut configured for installation to a case strut of an inlet case of a gas turbine engine. The probe strut includes one or more probes extending therefrom configured to measure one or more characteristics of an airflow past the one or more probes, a first attachment point configured to secure the probe strut to a hub portion of the inlet case, and a second attachment point configured to secure the probe strut to an outer case portion of the inlet case. A data acquisition module is located at a central longitudinal axis of the inlet and is operably connected to the probe to collect sensed data therefrom. The probe strut and the data acquisition module are configured to be installed, removed, and/or relocated without removal of the inlet case from the gas turbine engine.

First claim

What is claimed is:

1. A performance measurement system of an inlet of a gas turbine engine comprising:
a probe strut installed to a case strut of an inlet case of a gas turbine engine, including:
one or more probes extending therefrom configured to measure one or more characteristics of an airflow past the one or more probes;
a first attachment point configured to secure the probe strut to a hub portion of the inlet case; and
a second attachment point configured to secure the probe strut to an outer case portion of the inlet case;
a data acquisition module disposed at a central longitudinal axis of the inlet and operably connected to the probe to collect sensed data therefrom;
wherein the probe strut and the data acquisition module are configured to be installed, removed, and/or relocated without removal of the inlet case from the gas turbine engine.

2. The performance measurement system of claim 1 , wherein the probe strut is configured to be secured to the hub portion via one or more bolts.

3. The performance measurement system of claim 1 , wherein the probe strut is configured to be secured to the outer case portion via a pin.

4. The performance measurement system of claim 1 , wherein the probe is configured to measure one or more of temperature, steady state pressure, high response pressure, Mach number, or angle of attack.

5. The performance measurement system of claim 1 , further comprising two or more probe struts configured for installation to two or more case struts of the inlet case.

6. The performance measurement system of claim 5 , wherein:
a first probe strut of the two or more probe struts includes a first probe configured for a first measurement; and
a second probe strut of the two or more probe struts includes a second probe configured for a second measurement different from the first measurement.

7. An inlet assembly for a gas turbine engine comprising:
an inlet case including:
a hub portion;
an outer case portion; and
a plurality of case struts extending from the hub portion to the outer case portion; and
a performance measurement system including:
a probe strut installed to a case strut of plurality of case struts including:
one or more probes extending therefrom configured to measure one or more characteristics of an airflow past the one or more probes;
a first attachment point to secure the probe strut to the hub portion; and
a second attachment point to secure the probe strut to the outer case portion; and
a data acquisition module disposed at the hub portion and operably connected to the probe to collect sensed data therefrom;
wherein the probe strut and the data acquisition module are configured to be installed, removed, and/or relocated without removal of the inlet case from the gas turbine engine.

8. The inlet assembly of claim 7 , wherein the probe strut is secured to the hub portion via one or more bolts.

9. The inlet assembly of claim 7 , wherein the probe strut is secured to the outer case portion via a pin.

10. The inlet assembly of claim 7 , wherein the probe is configured to measure one or more of temperature, steady state pressure, high response pressure, Mach number, or angle of attack.

11. The inlet assembly of claim 7 , further comprising two or more probe struts installed to two or more case struts of the inlet case.

12. The inlet assembly of claim 11 , wherein:
a first probe strut of the two or more probe struts includes a first probe configured for a first measurement; and
a second probe strut of the two or more probe struts includes a second probe configured for a second measurement different from the first measurement.

13. The inlet assembly of claim 7 , further comprising a seal disposed between the case strut and the probe strut.

14. A gas turbine engine comprising:
a compressor section;
a combustor section;
a turbine section; and
an inlet section disposed upstream of the compressor section, including:
an inlet case including:
a hub portion;
an outer case portion; and
a plurality of case struts extending from the hub portion to the outer case portion; and
a performance measurement system including:
a probe strut installed to a case strut of plurality of case struts including:
one or more probes extending therefrom configured to measure one or more characteristics of an airflow past the one or more probes;
a first attachment point to secure the probe strut to the hub portion; and
a second attachment point to secure the probe strut to the outer case portion; and
a data acquisition module disposed at the hub portion and operably connected to the probe to collect sensed data therefrom;
wherein the probe strut and the data acquisition module are configured to be installed, removed, and/or relocated without removal of the inlet case from the gas turbine engine.

15. The gas turbine engine of claim 14 , wherein the probe strut is secured to the hub portion via one or more bolts.

16. The gas turbine engine of claim 14 , wherein the probe strut is secured to the outer case portion via a pin.

17. The gas turbine engine of claim 14 , wherein the probe is configured to measure one or more of temperature, steady state pressure, high response pressure, Mach number, or angle of attack.

18. The gas turbine engine of claim 14 , further comprising two or more probe struts installed to two or more case struts of the inlet case.

19. The gas turbine engine of claim 18 , wherein:
a first probe strut of the two or more probe struts includes a first probe configured for a first measurement; and
a second probe strut of the two or more probe struts includes a second probe configured for a second measurement different from the first measurement.

20. The gas turbine engine of claim 14 , further comprising a seal disposed between the case strut and the probe strut.

Assignees

• United Technologies Corp

Inventors

• Rice William W
• Covino Alfred F
• Hendricks Richard C
• Thomesen Douglas H
• Hackett Bryan J

Classifications

• F01D21/003 Primary

  Arrangements for testing or measuring (for measuring vibrations G01H) · CPC title

• F02C3/04

  having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) · CPC title

• F05D2240/121

  related to the leading edge of a stator vane · CPC title

• F01D17/08

  responsive to condition of working-fluid, e.g. pressure · CPC title

• F02C7/04

  Air intakes for gas-turbine plants or jet-propulsion plants · CPC title