Inlet performance measurement system for gas turbine engine

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.

BACKGROUND

Exemplary embodiments pertain to the art of gas turbine engines. More particularly, the present disclosure relates to measurement of performance characteristics of the gas turbine engine at the inlet.

During development and testing of gas turbine engine, it is desired to measure certain characteristics, such as pressures and/or temperatures at select locations of the gas turbine engine. The collected data is utilized to evaluate performance of the gas turbine engine, compared to an expected performance.

One such area of interest is the inlet of the gas turbine engine. Systems for measuring characteristics such as pressure and temperature at the inlet, however, are typically cumbersome to install and remove, and require significant amounts of disassembly and reassembly of the engine to repair to replace sensors or other components that may fail during operation. As such, the efficiency of the testing operation is greatly reduced.

BRIEF DESCRIPTION

In one embodiment, 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.

Additionally or alternatively, in this or other embodiments the probe strut is configured to be secured to the hub portion via one or more bolts.

Additionally or alternatively, in this or other embodiments the probe strut is configured to be secured to the outer case portion via a pin.

Additionally or alternatively, in this or other embodiments the probe is configured to measure one or more of temperature, steady state pressure, high response pressure, Mach number, or angle of attack.

Additionally or alternatively, in this or other embodiments two or more probe struts are configured for installation to two or more case struts of the inlet case.

Additionally or alternatively, in this or other embodiments 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.

In another embodiment, an inlet assembly for a gas turbine engine includes 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. The inlet assembly includes a performance measurement system including a probe strut installed to a case strut of plurality of case struts, 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 to secure the probe strut to the hub portion, and a second attachment point to secure the probe strut to the outer case portion. A data acquisition module is located at the hub portion 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.

Additionally or alternatively, in this or other embodiments the probe strut is secured to the hub portion via one or more bolts.

Additionally or alternatively, in this or other embodiments the probe strut is secured to the outer case portion via a pin.

Additionally or alternatively, in this or other embodiments the probe is configured to measure one or more of temperature, steady state pressure, high response pressure, Mach number, or angle of attack.

Additionally or alternatively, in this or other embodiments two or more probe struts are installed to two or more case struts of the inlet case.

Additionally or alternatively, in this or other embodiments 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.

Additionally or alternatively, in this or other embodiments a seal is positioned between the case strut and the probe strut.

In yet another embodiment, a gas turbine engine includes a compressor section, a combustor section, a turbine section, and an inlet section located upstream of the compressor section. The inlet section includes 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. The inlet section also includes a performance measurement system including a probe strut installed to a case strut of plurality of case struts. 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 to secure the probe strut to the hub portion, and a second attachment point to secure the probe strut to the outer case portion. A data acquisition module is located at the hub portion 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.

Additionally or alternatively, in this or other embodiments the probe strut is secured to the hub portion via one or more bolts.

Additionally or alternatively, in this or other embodiments the probe strut is secured to the outer case portion via a pin.

Additionally or alternatively, in this or other embodiments the probe is configured to measure one or more of temperature, steady state pressure, high response pressure, Mach number, or angle of attack.

Additionally or alternatively, in this or other embodiments two or more probe struts are installed to two or more case struts of the inlet case.

Additionally or alternatively, in this or other embodiments 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.

Additionally or alternatively, in this or other embodiments a seal is positioned between the case strut and the probe strut.

DETAILED DESCRIPTION

FIG. 1schematically illustrates a gas turbine engine20. The gas turbine engine20is disclosed herein as a turbojet engine that generally incorporates an inlet section22, a compressor section24, a combustor section26and a turbine section28. Alternative engines might include an augmentor section (not shown) among other systems or features. Further, while a turbojet configuration is illustrated and described herein, one skilled in the art will readily appreciate that the present disclosure may be readily utilized on other engine configurations, such as turbofan engines. The compressor section24drives air through the inlet section22and along a core flow path C for compression and communication into the combustor section26then expansion through the turbine section28.

The exemplary engine20generally includes a shaft30connecting the compressor section24and the turbine section28, with the shaft30mounted for rotation about an engine central longitudinal axis A relative to an engine static structure32via several bearing systems34. It should be understood that various bearing systems34at various locations may alternatively or additionally be provided, and the location of bearing systems34may be varied as appropriate to the application. Further, while a single shaft30is illustrated and described herein, other engines may utilize a two-spool configuration, with a first shaft connecting a high pressure compressor36to a high pressure turbine38, and a second shaft concentric to the first shaft connecting a low pressure compressor40to a low pressure turbine42.

The core airflow is compressed by the low pressure compressor40then the high pressure compressor36, mixed and burned with fuel in a combustor44of the combustor section26, then expanded over the high pressure turbine38and low pressure turbine42. The turbines38,42drive the shaft30in response to the expansion.

Referring now toFIG. 2, shown is a partial cross-sectional view of the inlet section22. The inlet section22includes an inlet case46located at the engine central longitudinal axis A. The inlet case46includes a hub portion48and an outer case portion50, with a plurality of case struts52extending from the hub portion48to the outer case portion50, with an inlet area of the core flowpath C defined between the hub portion48and the outer case portion50. In some embodiments, a nose cone54is provided at the hub portion48.

A performance measurement system56is installed on the inlet section22to obtain performance data regarding the inlet section22during operation of the engine20. The performance measurement system56includes a probe strut58located at one or more of the case struts52, in particular located over a case strut leading edge60, as shown best inFIG. 3. In some embodiments, a seal62is positioned between the probe strut58and the case strut52, providing an interface therebetween and preventing aerodynamic leakage between the probe strut58and the case strut52. The seal62extends along the probe strut58length and in some embodiments is formed from a silicone material. It is to be appreciated, however, that other seal configurations and/or seal materials may be utilized.

The probe strut58is configured with one or more probes64extending therefrom into the core airflow C. The probes64are configured to measure one or more of temperature, steady state pressure, high response pressure, side static at various flow angles at the same time. Further, the probes64may be configured to measure Mach number, angle of attack, or the like. The probes64extend through openings66formed in, for example, a probe strut leading edge68, and extend upstream from the probe strut leading edge68. The probes64are secured in the openings66via, for example, adhesive bonding, welding or brazing, mechanical fasteners such as a nut and bolt arrangement, or other means.

Referring toFIG. 4, the probe struts58may be located at selected case struts52of the plurality of case struts52to perform measurements at selected circumferential locations of the inlet section22, such as shown. In some embodiments, case struts52including probe struts58are alternated with case struts located at selected case struts52, while not located at other case struts52between the selected case struts52. Alternatively, other arrangements may be utilized, such as equipping each case strut52with a probe strut58, or equipping a single case strut52with a probe strut58.

The use of probe struts58installed at the case struts52provides flexibility in that the arrangement of probe struts58may be changed by adding probe struts58, removing probe struts58, and/or relocating probe struts58without the need for removal of the inlet case46from the engine20. Referring again toFIG. 2, the probe strut58is secured to the inlet case46at the outer case portion50via a strut pin70extending through the outer case portion50into the probe strut58.

The strut pin70arrangement is shown in more detail inFIGS. 5aand 5b. A pin holder72is secured to on outer surface74of the outer case portion50, via for example, fastener76. The strut pin70is secured in the pin holder72by, for example, a pin fastener84. The strut pin70extends radially inwardly from the pin holder72through a case pin opening78in the outer case portion50and into a strut pin opening80in the probe strut58. In some embodiments, the strut pin70includes a pin lip82to prevent the strut pin70from falling entirely through the pin opening80into the core flow path C.

Referring now toFIG. 5c, the inlet case46may be configured with strut pin openings80at each case strut52. In the event that a probe strut58is not installed at a selected case strut52, the pin opening80is closed via a plug84, which replaces the strut pin70in the pin holder72.

Referring again toFIG. 2, the probe strut58is secured to the hub portion48of the inlet case46via a support bracket86extending from a radially innermost portion of the probe strut58. Referring now toFIG. 6, the support bracket86is secured to a hub flange88of the hub portion48via at least one bolt or other fastener90extending through the support bracket86and into the hub flange88to secure the support bracket86to the hub flange88. In some embodiments, the support bracket86is formed integral to the probe strut58, while in other embodiments the components are formed separately and joined via a secondary process.

Referring again toFIG. 2, in some embodiments the performance measurement system56includes one or more data acquisition modules92located, for example, at the hub portion48of the inlet case46downstream of the nosecone54. The data acquisition modules92are connected to the probes64and are configured to collect the data sensed by the probes64and may perform processing operations on the collected data, and may perform other operations such as formatting or storage of the collected data. Further, the data acquisition modules92may include a communications module94to transmit the collected data over a wired or wireless connection to, for example, a computer (not shown). In the embodiments with a wired connection is utilized, the inlet case46may use one or more dummy struts through which wires and/or other components are installed to provide the wired interface between the data acquisition modules94and the computer.

The performance measurement systems56disclosed herein improve flexibility of data measurement and collection at the inlet section22because a variety of different probe combinations can be placed at various selected locations. This is due to the attachments at the outer case portion50and the hub portion48, which also allow the probe struts58to be removed, installed, and/or relocated without removal of the inlet case46from the engine20. It is also possible to remove the probe struts58and plug the pin openings80to configure the inlet case46as a non instrumented inlet case46. Further, by locating the data acquisition modules92at the hub portion48behind the nose cone54, the location is centralized thus reducing installation time, and equalize a length of pressure line utilized among the probe struts58for improved data consistency, and also allows for repair and replacement of the probe struts58without inlet case46or engine20removal.