Probe for a gas turbine engine

Abstract

A probe for measuring a flow parameter of a working fluid of a gas turbine engine includes a probe base, a probe head, and a probe body extending radially therebetween. A plurality of steady measurement channels extend from the probe base into the probe head. A plurality of steady measurement ports are defined at the probe head. Each steady measurement port is coupled to one steady measurement channel and is in flow communication with a steady pressure sensor to measure a steady pressure of the working fluid. A fast response measurement channel extends from the probe base into the probe head and coupled to a fast response measurement port defined at the probe head. A fast response pressure sensor is positioned within the fast response measurement channel to measure an instantaneous pressure of the working fluid at a fast response frequency.

Description

Docket No. 2025PF00223PROBE FOR A GAS TURBINE ENGINEBACKGROUND

[0001] A gas turbine engine typically includes a compressor section, a turbine section, and a combustion section disposed therebetween. The compressor section typically includes multiple stages of compressor blades and compressor vanes to produce compressed air. The combustion section typically includes a plurality of combustors to produce hot working fluid by combusting mixture of the compressed air and fuel. The turbine section typically includes multiple stages of turbine blades and turbine vanes to expand the hot working fluid and to convert fluid energy to mechanical energy. A probe may be used in the gas turbine engine to measure flow parameters of the hot working fluid, such as pressure, temperature, during an operation of the gas turbine engine.SUMMARY

[0002] In one aspect, a probe is provided. The probe is usable to measure a flow parameter of a working fluid of a gas turbine engine. The probe includes a probe base, a probe head, and a probe body extending from the probe base to the probe head defining a radial direction. A plurality of steady measurement channels extend from the probe base into the probe head. A plurality of steady measurement ports are defined at the probe head. Each steady measurement port of the plurality of steady measurement ports is coupled to one steady measurement channel of the plurality of steady measurement channels. A plurality of steady pressure sensors, each steady pressure sensor of the plurality of steady pressure sensors being in flow communication with one steady measurement port of the plurality of steady measurement ports to measure a steady pressure of the working fluid. A fast response measurement channel extends from theDocket No. 2025PF00223probe base into the probe head. A fast response measurement port is defined at the probe head and coupled to the fast response measurement channel. A fast response pressure sensor is disposed within the fast response measurement channel to measure an instantaneous pressure of the working fluid at a fast response frequency.

[0003] In one aspect, a method for manufacturing a probe is provided. The method includes positioning a foundation member to place a foundation surface in a horizontal direction, and adding a plurality of layers to the foundation surface to define the probe, a first layer applied directly to the foundation surface, and each subsequent layer applied to a prior subsequent layer, the plurality of layers cooperating to define a plurality of steady measurement channels extending from a probe base into a probe head, a plurality of steady measurement ports defined at the probe head and each steady measurement port coupled to one steady measurement channel of the plurality of steady measurement channels, a fast response measurement channel extending from the probe base into the probe head, and a fast response measurement port defined at the probe head and coupled to the fast response measurement channel.BRIEF DESCRIPTION OF THE DRAWINGS

[0004] To easily identify the discussion of any particular element or act, the most significant digit or digits in a reference number refer to the figure number in which that element is first introduced.

[0005] FIG. 1 illustrates a longitudinal cross-sectional view of a gas turbine engine taken along a plane that contains a longitudinal axis.

[0006] FIG. 2 illustrates a perspective view of a probe usable in the gas turbine engine of FIG. 1.

[0007] FIG. 3 illustrates a different perspective view of the probe of FIG. 2.

[0008] FIG. 4 illustrates a transparent perspective view of the probe of FIG. 2.Docket No. 2025PF00223

[0009] FIG. 5 illustrates a cross-sectional view of the probe of FIG. 2 along a section plane 5-5.

[0010] FIG. 6 illustrates a cross-sectional view of the probe of FIG. 2 along a section plane 6-6.

[0011] FIG. 7 illustrates a flow chart of a method for manufacturing the probe of FIG. 2.DETAILED DESCRIPTION

[0012] Before any embodiments of the invention are explained in detail, it is to be understood that the invention is not limited in its application to the details of construction and the arrangement of components set forth in this description or illustrated in the following drawings. The invention is capable of other embodiments and of being practiced or of being carried out in various ways. Also, it is to be understood that the phraseology and terminology used herein is for the purpose of description and should not be regarded as limiting.

[0013] Various technologies that pertain to systems and methods will now be described with reference to the drawings, where like reference numerals represent like elements throughout. The drawings discussed below, and the various embodiments used to describe the principles of the present disclosure in this patent document are by way of illustration only and should not be construed in any way to limit the scope of the disclosure. Those skilled in the art will understand that the principles of the present disclosure may be implemented in any suitably arranged apparatus. It is to be understood that functionality that is described as being carried out by certain system elements may be performed by multiple elements. Similarly, for instance, an element may be configured to perform functionality that is described as being carried out by multiple elements. The numerous innovative teachings of the present application will be described with reference to exemplary non-limiting embodiments.Docket No. 2025PF00223

[0014] It should be understood that the words or phrases used herein should be construed broadly, unless expressly limited in some examples. For example, the terms “including”, “having”, and “comprising”, as well as derivatives thereof, mean inclusion without limitation. The singular forms “a”, “an”, and “the” are intended to include the plural forms as well, unless the context clearly indicates otherwise. Further, the term “and / or” as used herein refers to and encompasses any and all possible combinations of one or more of the associated listed items. The term “or” is inclusive, meaning and / or, unless the context clearly indicates otherwise. The phrases “associated with” and “associated therewith” as well as derivatives thereof, may mean to include, be included within, interconnect with, contain, be contained within, connect to or with, couple to or with, be communicable with, cooperate with, interleave, juxtapose, be proximate to, be bound to or with, have, have a property of, or the like. Furthermore, while multiple embodiments or constructions may be described herein, any features, methods, steps, components, etc. described with regard to one embodiment are equally applicable to other embodiments absent a specific statement to the contrary.

[0015] Although the terms “first”, “second”, “third” and so forth may be used herein to refer to various elements, information, functions, or acts, these elements, information, functions, or acts should not be limited by these terms. Rather these numeral adjectives are used to distinguish different elements, information, functions or acts from each other. For example, a first element, information, function, or act could be termed a second element, information, function, or act, and, similarly, a second element, information, function, or act could be termed a first element, information, function, or act, without departing from the scope of the present disclosure.

[0016] In the description, the terms “axial” or “axially” refer to a direction along a longitudinal axis of a gas turbine engine. The terms “radial” or “radially” refer to a direction perpendicular to the longitudinal axis of the gas turbine engine. The terms “downstream” or “aft” refer to a direction along a flow direction. The terms “upstream” or “forward” refer to a direction against the flow direction.Docket No. 2025PF00223

[0017] In addition, the term “adjacent to" may mean that an element is relatively near to but not in contact with a further element or that the element is in contact with the further portion, unless the context clearly indicates otherwise. Further, the phrase “based on” is intended to mean “based, at least in part, on” unless explicitly stated otherwise. Terms “about” or “substantially” or like terms are intended to cover variations in a value that are within normal industry manufacturing tolerances for that dimension. If no industry standard is available, a variation of twenty percent would fall within the meaning of these terms unless otherwise stated.

[0018] FIG. 1 illustrates an example of a gas turbine engine 100 including a compressor section 102, a combustion section 104, and a turbine section 106 arranged along a longitudinal axis 108. The compressor section 102 includes a plurality of compressor stages 110 with each compressor stage 110 including a set of compressor vanes 112 or adjustable guide vanes and a set of compressor blades 114. The compressor vanes 112 are stationary and the compressor blades 114 are rotating during operation. A rotor 116 supports the compressor blades 114 for rotation about the longitudinal axis 108 during operation. In some constructions, a single one-piece rotor 116 extends the length of the gas turbine engine 100 and is supported for rotation by a bearing at either end. In other constructions, the rotor 116 is assembled from several separate spools that are attached to one another or may include multiple disk sections that are attached via a bolt or plurality of bolts.

[0019] The compressor section 102 is in fluid communication with an inlet section 118 to allow the gas turbine engine 100 to draw atmospheric air into the compressor section 102. During operation of the gas turbine engine 100, the compressor section 102 draws in atmospheric air and compresses that air for delivery to the combustion section 104. The illustrated compressor section 102 is an example of one compressor section 102 with other arrangements and designs being possible.

[0020] In the illustrated construction, the combustion section 104 includes a plurality of separate combustors 120 that each operate to mix a flow of fuel with the compressed air from the compressor section 102 and to combust that air-fuel mixture to produce a flowDocket No. 2025PF00223of high temperature, high pressure combustion gas or working fluid 122. Of course, many other arrangements of the combustion section 104 are possible.

[0021] The turbine section 106 includes a plurality of turbine stages 124 with each turbine stage 124 including a number of turbine vanes 126 and a number of turbine blades 128. The turbine vanes 126 are stationary and the turbine blades 128 are rotating during operation. The turbine stages 124 are arranged to receive the working fluid 122 from the combustion section 104 at a turbine inlet 130 and expand that gas to convert thermal and pressure energy into rotating or mechanical work. The turbine section 106 is connected to the compressor section 102 to drive the compressor section 102. For gas turbine engines 100 used for power generation or as prime movers, the turbine section 106 is also connected to a generator, pump, or other device to be driven. As with the compressor section 102, other designs and arrangements of the turbine section 106 are possible.

[0022] An exhaust portion 132 is positioned downstream of the turbine section 106 and is arranged to receive the expanded flow of working fluid 122 from the final turbine stage 124 in the turbine section 106. The exhaust portion 132 is arranged to efficiently direct the working fluid 122 away from the turbine section 106 to assure efficient operation of the turbine section 106. Many variations and design differences are possible in the exhaust portion 132. As such, the illustrated exhaust portion 132 is but one example of those variations.

[0023] A control system 134 is coupled to the gas turbine engine 100 and operates to monitor various operating parameters and to control various operations of the gas turbine engine 100. In preferred constructions the control system 134 is typically microprocessor based and includes memory devices and data storage devices for collecting, analyzing, and storing data. In addition, the control system 134 provides output data to various devices including monitors, printers, indicators, and the like that allow users to interface with the control system 134 to provide inputs or adjustments. In the example of a power generation system, a user may input a power output set point and the controlDocket No. 2025PF00223system 134 may adjust the various control inputs to achieve that power output in an efficient manner.

[0024] The control system 134 can control various operating parameters including, but not limited to variable inlet guide vane positions, fuel flow rates and pressures, engine speed, valve positions, generator load, and generator excitation. Of course, other applications may have fewer or more controllable devices. The control system 134 also monitors various parameters to assure that the gas turbine engine 100 is operating properly. Some parameters that are monitored may include inlet air temperature, compressor outlet temperature and pressure, combustor outlet temperature, fuel flow rate, generator power output, bearing temperature, and the like. Many of these measurements are displayed for the user and are logged for later review should such a review be necessary.

[0025] A casing 136 encloses the combustor 120, the turbine vanes 126, and the turbine blades 128. The working fluid 122 is enclosed within the casing 136. A probe 200 is fixed to the casing 136 and disposed within the casing 136. The probe 200 measures flow parameters of the working fluid 122 during operation. The flow parameters include steady pressure and instantaneous pressure of the working fluid 122. The working fluid 122 has a temperature that exceeds 500°C and can achieve 2000°C or even higher. The probe 200 is made of nickel based super alloy, for example, Inconel® 718, so that the probe 200 can withstand the high temperature of the working fluid 122. In the construction illustrated in FIG. 1, the probe 200 is disposed adjacent to and downstream of the last stage of the turbine blades 128. In other constructions, the probe 200 may be disposed in any locations as desired.

[0026] FIG. 2 illustrates a first perspective view of the probe 200 from a first view direction. The probe 200 has a probe base 202, a probe head 204, and a probe body 206 extending from the probe base 202 to the probe head 204 defining a radial direction 208. The probe base 202 has a base surface 210 that defines the outermost surface of the probe 200. The probe base 202 has a cylindrical shape. The probe body 206 has a truncated conical shape. The probe head 204 has a head body 212 connected to a head tip 214.Docket No. 2025PF00223The head body 212 has a cylindrical shape. The head tip 214 has a semi-spherical tip that defines the innermost surface of the probe 200. The probe base 202, the probe head 204, and the probe body 206 are coaxial. In other constructions, the probe 200 may have other geometries as desired.

[0027] A fast response measurement channel 216 is disposed within the probe 200. The fast response measurement channel 216 extends from the base surface 210 into the probe head 204. A fast response measurement port 218 is defined at the probe head 204 and coupled to the fast response measurement channel 216. In the construction illustrated in FIG. 2, the fast response measurement port 218 is defined at the head body 212. A diameter of the fast response measurement port 218 is in a range of 0.05 mm to 3 mm, or in a range of 0.1 mm to 2 mm, or in a range of 0.3 mm to 1 mm. In other constructions, the fast response measurement port 218 may be positioned at any locations or have other dimensions as desired.

[0028] A plurality of steady measurement channels 220 are disposed within the probe 200 and circumferentially around the fast response measurement channels 216. The plurality of steady measurement channels 220 extend from the base surface 210 into the probe head 204. A plurality of steady measurement ports 222 are defined at the probe head 204. Each steady measurement port 222 of the plurality of steady measurement ports 222 is coupled to one steady measurement channel 220 of the plurality of steady measurement channels 220. The plurality of steady measurement ports 222 are disposed closer to the head tip 214 than the fast response measurement port 218 in the radial direction 208. In the construction illustrated in FIG. 2, the probe 200 has four steady measurement channels 220 and four steady measurement ports 222. The four steady measurement ports 222 include a reference steady measurement port 224 defined at the head body 212, a first pitch steady measurement ports 226 defined at the head body 212, a second pitch steady measurement port 228 defined at the head body 212, and a yaw steady measurement port 230 defined at the head tip 214. The first pitch steady measurement port 226 and the second pitch steady measurement port 228 are positioned at two circumferential sides of the reference steady measurement port 224. A diameter of each steady measurement port 222 is in a range of 0.05 mm to 3 mm, or in a range of 0.1Docket No. 2025PF00223mm to 2 mm, or in a range of 0.3 mm to 1 mm. In other constructions, the probe 200 may have less or more than four steady measurement channels 220 and steady measurement ports 222 as desired, or each steady measurement port 222 may have other dimensions as desired.

[0029] A temperature measurement channel 232 extends from the base surface 210 into the probe head 204. In the construction illustrated in FIG. 2, the temperature measurement channel 232 is disposed between the plurality of steady measurement channels 220. Two steady measurement channels 220 are positioned at one circumferential side of the temperature measurement channel 232. The other two steady measurement channels 220 are positioned at the other circumferential side of the temperature measurement channel 232. In other constructions, the temperature measurement channel 232 may be positioned at any desired locations.

[0030] FIG. 3 illustrates a second perspective view of the probe 200 from a second view direction that is different from the first viewing direction in FIG. 2. The temperature measurement channel 232 extends from the base surface 210 into an of the probe base 202 and an interior of the probe body 206. The temperature measurement channel 232 extends from the interior of the probe body 206 to an outer surface 302 of the head body 212. The temperature measurement channel 232 extends along the outer surface 302 toward the head tip 214 and then extends into an interior of the head body 212. The temperature measurement channel 232 defines a dent 304 along the outer surface 302.

[0031] The probe body 206 has a first side 306 and a second side 308. The first side 306 connects to the probe base 202. The second side 308 connects to the probe head 204. The first side 306 has a diameter that is larger than a diameter of the second side 308. The diameter of the first side 306 defines the maximum diameter 310 of the probe 200. The maximum diameter 310 is in a range of 10 mm to 50 mm. The diameter of the head body 212 defines the minimum diameter 312 of the probe 200. The minimum diameter 312 is in a range of 5 mm to 20 mm.

[0032] FIG. 4 illustrates a transparent perspective view of the probe 200. Each steady measurement channel 220 is in fluid communication with a steady pressure sensor 402 toDocket No. 2025PF00223measure a steady pressure of the working fluid 122. In the construction illustrated in FIG. 4, the plurality of steady pressure sensors 402 are disposed outside of the probe 200. The plurality of steady pressure sensors 402 are disposed remotely from the probe 200, for example, more than 10 m away from the probe 200. In other construction, the plurality of steady pressure sensors 402 may be disposed within the probe 200, or within a shaft of the probe 200, or any suitable locations. The steady pressure sensors 402 includes a piezoresitive sensor.

[0033] The plurality of steady measurement channels 220 and the temperature measurement channel 232 are disposed within the probe 200. Each steady measurement channel 220 has a continuous nonlinear shape within the interior of the probe 200.

[0034] FIG. 5 illustrates a cross-sectional view of the probe 200 along a section plane 5-5 of FIG. 2. The temperature measurement channel 232 has a continuous nonlinear shape and extends in the interior of the probe base 202 and the probe body 206. The temperature measurement channel 232 extends into the interior of the probe head 204 from the outer surface 302 of the head body 212. A temperature sensor 502 is positioned within the temperature measurement channel 232 and at a location within the probe head 204. The temperature sensor 502 measures a temperature of the working fluid 122.

[0035] The fast response measurement channel 216 has a tube 504 and a cavity 506. The tube 504 and the cavity 506 are disposed at the interior of the probe head 204. The tube 504 connects the cavity 506 with the fast response measurement port 218. In the construction illustrated in FIG. 5, the cavity 506 has a conical shape. In other constructions, the cavity 506 may have other shapes as desired.

[0036] A fast response pressure sensor 508 is disposed within the fast response measurement channel 216 to an instantaneous pressure of the working fluid 122 at a fast response frequency. The fast response pressure sensor 508 includes a cable 510 and a fast response pressure transducer 512 that is connected to the cable 510 and in contact with the cavity 506. The fast response pressure transducer 512 is engaged with the fast response measurement channel 216 by a thread engagement 514. The fast response frequency of the fast response pressure sensor 508 is equal to or above 1 kHz. ForDocket No. 2025PF00223example, the fast response frequency is in a range of 1 kHz to 100 kHz, or in a range of 2 kHz to 90 kHz, or in a range of 5 kHz to 80 kHz, etc. A diameter of the fast response pressure transducer 512 is in a range of 1 mm to 10 mm, or in a range of 2 mm to 8 mm, or in a range of 3 mm to 6 mm, etc. The fast response pressure sensor 508 is made of nickel based super alloy, for example, Inconel® 718, so that the fast response pressure sensor 508 can withstand the high temperature of the working fluid 122. The fast response pressure sensor 508 includes a piezoresitive sensor.

[0037] The fast response measurement port 218 and the plurality of steady measurement ports 222 are disposed at an upstream side 516 of the probe 200 facing the flow direction of the working fluid 122. The temperature sensor 502 is positioned closer to the upstream side 516 than a downstream side 518 of the probe 200 facing away from the flow direction of the working fluid 122.

[0038] The probe 200 has a probe central axis 520 in the radial direction 208. The fast response measurement channel 216 has a channel central axis 522 in the radial direction 208. The channel central axis 522 is offset from the probe central axis 520 toward to the upstream side 516 so that the fast response pressure sensor 508 is disposed close to the fast response measurement port 218.

[0039] The yaw steady measurement port 230 has a yaw port central axis 524. A yaw angle 526 is defined between the yaw port central axis 524 and the probe central axis 520. In the construction illustrated in FIG. 5, the yaw angle 526 is 45 degrees. In other constructions, the yaw angle 526 may be less or more than 45 degrees.

[0040] The probe 200 is manufactured by additive manufacturing process, or other suitable manufacturing methods to achieve the complex internal geometry and maintain a miniature size. In one construction, a selective laser melting process is used to manufacture the probe 200 in a layer-by-layer process.

[0041] FIG. 6 illustrates a cross-sectional view of the probe 200 along a section plane 6-6 of FIG. 2. The reference steady measurement port 224 has a reference port central axis 602 that is parallel to the flow direction of the working fluid 122. The first pitch steadyDocket No. 2025PF00223measurement port 226 and the second pitch steady measurement port 228 are positioned at two circumferential sides of the reference steady measurement port 224.

[0042] The first pitch steady measurement port 226 has a first pitch port central axis 604. The second pitch steady measurement port 228 has a second pitch port central axis 606. A first pitch angle 608 is defined between the first pitch port central axis 604 and the reference port central axis 602. A second pitch angle 610 is defined between the second pitch port central axis 606 and the reference port central axis 602. In the construction illustrated in FIG. 6, the first pitch angle 608 and the second pitch angle 610 are 45 degrees. In other constructions, the first pitch angle 608 and the second pitch angle 610 may be less or more than 45 degrees.

[0043] FIG. 7 illustrates a flow chart of a method 700 for manufacturing the probe 200. The method 700 uses an additive manufacturing process such as or similar to a selective laser melting process.

[0044] In step 702, a foundation member is positioned to place a foundation surface in a horizontal direction. In step 704, a plurality of layers are added to the foundation surface to define the probe 200. A first layer is applied directly to the foundation surface. Each subsequent layer is applied to a prior subsequent layer. The plurality of layers cooperate to define the plurality of steady measurement channels 220 extending from the probe base 202 into the probe head 204, a plurality of steady measurement ports 222 defined at the probe head 204 and each steady measurement port 222 coupled to one steady measurement channel 220 of the plurality of steady measurement channels 220, a fast response measurement channel extending from the probe base into the probe head, and a fast response measurement port defined at the probe head and coupled to the fast response measurement channel.

[0045] During operation, the probe 200 is positioned adjacent to and downstream of the last stage of the turbine blades 128 to measure flow parameters of the working fluid 122. The temperature sensor 502 measure temperature of the working fluid 122. The steady pressure sensors 402 measure the steady pressure of the working fluid 122 that flows into the steady measurement channels 220 through the steady measurement ports 222. TheDocket No. 2025PF00223steady pressure sensor 402 coupled with the reference steady measurement port 224 measures the steady pressure of the working fluid 122 having zero angle with respect to the flow direction of the working fluid 122. The steady pressure sensor 402 coupled with the first pitch steady measurement port 226 measures the steady pressure of the working fluid 122 having the first pitch angle 608 with respect to the flow direction of the working fluid 122. The steady pressure sensor 402 coupled with the second pitch steady measurement port 228 measures the steady pressure of the working fluid 122 having the second pitch angle 610 with respect to the flow direction of the working fluid 122. The steady pressure sensor 402 coupled with the yaw steady measurement port 230 measures the steady pressure of the working fluid 122 having the yaw angle 526 with respect to the flow direction of the working fluid 122. The probe 200 is rotated at every measurement point. The measured steady pressures at different measurement points are averaged to obtain a reference steady pressure having zero angle with respect to the flow direction of the working fluid 122.

[0046] The fast response pressure sensor 508 measures the instantaneous pressure of the working fluid 122 that flows into the fast response measurement channel 216 through the fast response measurement port 218. The fast response pressure sensor 508 measures the instantaneous pressure of the working fluid 122 at the fast response frequency. The fast response frequency is in a range of 1 kHz to 100 kHz. The channel central axis 522 is offset from the probe central axis 520 toward the upstream side 516 so that the fast response pressure sensor 508 is positioned close to the fast response measurement port 218 to achieve the fast response frequency. The cavity 506 has a conical shape that allows the pressure to be distributed over the fast response pressure transducer 512 and also achieve the fast response frequency.

[0047] The probe 200 and the fast response pressure sensor 508 are made of nickel based super alloy, for example, Inconel® 718, so that the probe 200 and the fast response pressure sensor 508 can withstand the high temperature of the working fluid 122. The temperature of the working fluid 122 is in a range of 500°C to 2000°C.Docket No. 2025PF00223

[0048] The maximum diameter of the probe 200 is in a range of in a range of 10 mm to 50 mm. The miniature size of the probe 200 reduces the blockage of the working fluid 122 during operation which improves measurement precision.

[0049] The steady measurement channels 220 and the temperature measurement channel 232 have continuous nonlinear shapes so that they can be disposed within the probe 200 and around the fast response measurement channel 216. The complex internal geometry within the probe 200 enhances sensitivity and robustness of the probe 200 and improves accuracy and reliability of the flow parameter measurements under a harsh condition. The flow parameters acquired by the probe 200 facilitates analysis of transient aerodynamic phenomena, such as shock structures and flow instabilities, reduces acoustic emissions, and provides experimental data to validate computational fluid dynamic simulations. The probe 200 is manufactured by additive manufacturing process to achieve the complex internal geometry and reliable performance while maintaining a miniature size.

[0050] Although an exemplary embodiment of the present disclosure has been described in detail, those skilled in the art will understand that various changes, substitutions, variations, and improvements disclosed herein may be made without departing from the spirit and scope of the disclosure in its broadest form.

[0051] None of the description in the present application should be read as implying that any particular element, step, act, or function is an essential element, which must be included in the claim scope: the scope of patented subject matter is defined only by the allowed claims. Moreover, none of these claims are intended to invoke a means plus function claim construction unless the exact words "means for" are followed by a participle.

Claims

Docket No. 2025PF00223CLAIMSWhat is claimed is:

1. A probe usable to measure a flow parameter of a working fluid of a gas turbine engine, the probe comprising:a probe base;a probe head;a probe body extending from the probe base to the probe head defining a radial direction;a plurality of steady measurement channels extending from the probe base into the probe head;a plurality of steady measurement ports defined at the probe head, each steady measurement port of the plurality of steady measurement ports coupled to one steady measurement channel of the plurality of steady measurement channels;a plurality of steady pressure sensors, each steady pressure sensor of the plurality of steady pressure sensors being in flow communication with one steady measurement port of the plurality of steady measurement ports to measure a steady pressure of the working fluid;a fast response measurement channel extending from the probe base into the probe head;a fast response measurement port defined at the probe head and coupled to the fast response measurement channel; anda fast response pressure sensor disposed within the fast response measurement channel to measure an instantaneous pressure of the working fluid at a fast response frequency.

2. The probe of claim 1, wherein the fast response measurement channel comprises a cavity and a tube, and wherein the tube connects the cavity with the fast response measurement port.

3. The probe of claim 2, wherein the cavity has a conical shape.Docket No. 2025PF002234. The probe of claim 2, wherein the fast response pressure sensor comprises a cable and a fast response pressure transducer connected to the cable, and wherein the fast response pressure transducer is in contact with the cavity.

5. The probe of claim 4, wherein a diameter of the fast response pressure transducer is in a range of 1 mm to 10 mm.

6. The probe of claim 1, wherein a channel central axis of the fast response measurement channel is offset from a probe central axis toward an upstream side of the probe.

7. The probe of claim 1, wherein the plurality of steady measurement ports and the fast response measurement port are positioned at an upstream side of the probe.

8. The probe of claim 1, wherein the plurality of steady measurement ports comprises a reference steady measurement port having a reference port central axis that is parallel to a flow direction of the working fluid, a first pitch steady measurement port, a second pitch steady measurement port, and a yaw steady measurement port, wherein the first pitch steady measurement port and the second pitch steady measurement port are positioned at two circumferential sides of the reference steady measurement port, and wherein the yaw steady measurement port is positioned having a yaw angle with respect to a probe central axis.

9. The probe of claim 1, further comprising a temperature measurement channel extending from the probe base into the probe head, wherein the temperature measurement channel has a continuous nonlinear shape.

10. The probe of claim 9, further comprising a temperature sensor disposed within the temperature measurement channel, wherein the temperature sensor is disposed closer to an upstream side than a downstream side.

11. The probe of claim 9, wherein the temperature measurement channel extends in an interior of the probe base and the head body, extends along an outer surface of the probe head, and extends into an interior of the probe head.Docket No. 2025PF0022312. The probe of claim 1, wherein the fast response pressure sensor is engaged with the fast response measurement channel by a thread engagement.

13. The probe of claim 1, wherein the fast response frequency is in a range of 1 kHz to 100 kHz.

14. The probe of claim 1, wherein a temperature of the working fluid is in a range of 500°C to 2000°C.

15. The probe of claim 1, wherein the maximum diameter of the probe is in a range of 10 mm to 50 mm.

16. The probe of claim 1, wherein each steady measurement channel of the plurality of steady measurement channels has a continuous nonlinear shape.

17. A method for manufacturing a probe, the method comprising: positioning a foundation member to place a foundation surface in a horizontal direction; andadding a plurality of layers to the foundation surface to define the probe, a first layer applied directly to the foundation surface, and each subsequent layer applied to a prior subsequent layer, the plurality of layers cooperating to define a plurality of steady measurement channels extending from a probe base into a probe head, a plurality of steady measurement ports defined at the probe head and each steady measurement port coupled to one steady measurement channel of the plurality of steady measurement channels, a fast response measurement channel extending from the probe base into the probe head, and a fast response measurement port defined at the probe head and coupled to the fast response measurement channel.

18. The method of claim 17, wherein the fast response measurement channel is formed having a tube and a cavity, wherein the tube connects the cavity with the fast response measurement port, and wherein the cavity has a conical shape.

19. The method of claim 17, wherein the fast response measurement channel is formed having a channel central axis that is offset from a probe central axis toward oneDocket No. 2025PF00223side of the probe, and wherein the plurality of steady measurement ports and the fast response measurement port are formed at the one side of the probe.

20. The method of claim 17, further comprising forming a temperature measurement channel extending from the probe base into the probe head and having a continuous nonlinear shape.

21. The method of claim 17, wherein the plurality of steady measurement ports are formed having a reference steady measurement port, a first pitch steady measurement port, a second pitch steady measurement port, and a yaw steady measurement port, wherein the first pitch steady measurement port and the second pitch steady measurement port are formed at two circumferential sides of the reference steady measurement port, and wherein the yaw steady measurement port is formed having a yaw angle with respect to a probe central axis.

22. The method of claim 17, wherein each steady measurement channel of the plurality of steady measurement channels is formed having a continuous nonlinear shape.

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