Direct horsepower and torque measurement system for gas turbine engine
A sensor arrangement for a gas powered turbine includes at least one sensor disposed on a power extraction shaft and configured to output a measured power extraction of the power extraction shaft. A controller is in communication with the at least one sensor. The controller includes a memory and a processor. The memory stores instructions for causing the processor to respond to a received measured power extraction of the power extraction shaft by synthesizing an instantaneous engine power output and engine efficiency and adjusting at least one parameter of the engine based on the synthesized engine power output and engine efficiency.
1. A sensor arrangement for a gas powered turbine comprising:
at least one sensor disposed on a power extraction shaft and configured to output a measured power extraction of the power extraction shaft, wherein the power extraction shaft extracts power from at least one spool and provides the power to at least one additional engine system;
a controller in communication with the at least one sensor, the controller including a memory and a processor, the memory storing instructions for causing the processor to respond to a received measured power extraction of the power extraction shaft by synthesizing an instantaneous engine power output from the measured power extraction and an engine efficiency from the measured power extraction and adjusting at least one parameter of the engine based on the synthesized engine power output and engine efficiency.
2. The sensor arrangement of claim 1 , wherein the at least one sensor is disposed on a tower shaft, the tower shaft being interfaced with a turbine shaft of the gas powered turbine via a gear system.
3. The sensor arrangement of claim 2 , wherein the at least one engine parameter includes a variable vane angle of at least one compressor stage.
4. The sensor arrangement of claim 1 , wherein the at least one sensor is disposed on an aircraft mounted accessory drive shaft.
5. The sensor arrangement of claim 4 , wherein the at least one engine parameter includes a variable blade angle of a plurality of fan blades in at least one stage of a fan of the gas powered turbine.
6. The sensor arrangement of claim 1 , wherein the at least one sensor is at least one of a torque sensor and a horsepower sensor.
7. The sensor arrangement of claim 1 , wherein the at least one sensor is in wireless communication with the power extraction shaft.
8. The sensor arrangement of claim 1 , wherein the engine power is synthesized using a control model including inputs of at least one measured power extraction, the at least one measured power extraction being sourced from a singular component attached to the power extraction shaft, with a power extraction of a remainder of components extracting power via the power extraction shaft being synthesized.
9. The sensor arrangement of claim 1 , wherein the gas powered turbine is a geared turbofan aircraft engine.
10. A gas powered turbine comprising:
a primary fluid flowpath connecting a compressor section, a combustor section, and a turbine section, the compressor section including a first compressor and a second compressor, with the second compressor operating at a higher pressure than the first compressor, the turbine section including a first turbine and a second turbine with the second turbine operating at a higher pressure than the first turbine;
a first shaft connecting the first compressor section with the first turbine section, such that rotation of the first turbine section drives rotation of the first compressor section;
a second shaft connecting the second compressor section with the second turbine section, such that rotation of the second turbine section drives rotation of the first compressor section;
a first power extraction shaft interfaced with one of the first shaft and the second shaft, such that rotation of the one of the first shaft and the second shaft is translated to the first power extraction shaft;
a first sensor disposed on the first power extraction shaft and configured to monitor and output a measured power extraction of the first power extraction shaft, wherein the first power extraction shaft extracts power from the one of the first shaft and the second shaft and provides the extracted power to at least one additional engine system; and
a controller in communication with the first sensor, the controller including a processor and a memory with the memory storing instructions for causing the processor to respond to a received measured power extraction of the first power extraction shaft by synthesizing an instantaneous engine power output from the measured power extraction and synthesizing an engine efficiency based on the measured power extraction of the first power extraction shaft and adjusting at least one parameter of the engine based on the synthesized engine power output and engine efficiency.
11. The gas turbine engine of claim 10 , further comprising a second power extraction shaft, the second power extraction shaft being interfaced with the other of the first shaft and the second shaft such that rotation of the other of the first shaft and the second shaft is translated to the second power extraction shaft, and a second sensor disposed on the second power extraction shaft and configured to monitor and output a measured power extraction of the second power extraction shaft.
12. The gas turbine engine of claim 11 , wherein synthesizing an instantaneous engine power output and engine efficiency is further based on the measured power extraction of the second power extraction shaft.
13. The gas turbine engine of claim 12 , wherein the engine power is synthesized using a control model including inputs of at least one measured power extraction, the at least one measured power extraction being sourced from a singular component attached to the power extraction shaft, with a power extraction of a remainder of components extracting power via the power extraction shaft being synthesized.
14. The gas turbine engine of claim 12 , wherein the first power extraction shaft is a tower shaft interfaced with the second shaft via a gear system.
15. The gas turbine engine of claim 14 , wherein the first sensor is at least one of a torque sensor and a horse power sensor, and wherein the at least one parameter of the engine is a variable vane angle of at least one compressor stage in the compressor section.
16. The gas turbine engine of claim 12 , wherein the first power extraction shaft is an aircraft mounted accessory drive shaft.
17. The gas turbine engine of claim 16 , wherein the at least one parameter of the engine is a variable fan blade angle of at least one stage of an engine fan driven by the first shaft.
18. A method for controlling at least one engine parameter of a gas turbine engine comprising:
measuring an output power of at least a first power extraction shaft of a gas turbine engine using a sensor physically disposed on the first power extraction shaft, wherein the first power extraction shaft extracts power from at least one spool and provides the power to at least one additional engine system;
synthesizing an instantaneous engine power output from the measured power extraction and synthesizing an engine efficiency of the gas turbine engine based on the measured output power; and
adjusting at least one engine parameter based on the synthesized instantaneous engine power output and engine efficiency.
19. The method of claim 18 , further comprising measuring an output power of at least a second power extraction shaft of a gas turbine engine using a sensor physically disposed on the second power extraction shaft and synthesizing the instantaneous engine power output and engine efficiency of the gas turbine engine based on the measured output power from the first sensor and the second sensor.
20. The method of claim 18 , wherein the first power extraction shaft is one of a tower shaft interfaced with a high speed spool of the gas turbine engine and an aircraft mounted accessory shaft interfaced with a low speed spool of the gas turbine engine.