Method of operating a turbine engine having a bleed system
A method of operating a turbine engine. The turbine engine includes a high-pressure compressor including a high-pressure compressor flowpath and a plurality of stages, and a bleed system. The bleed system includes a plurality of bleed flowpaths including a first bleed flowpath from one stage of the plurality of stages and a second bleed flowpath from another stage of the plurality of stages. The method includes directing compressed air through the high-pressure compressor flowpath, directing a first portion of the compressed air through the first bleed flowpath, the first portion of the compressed air having a first mass flow, directing a second portion of the compressed air through the second bleed flowpath, determining an altitude of the turbine engine, and changing the first mass flow of the first portion of the compressed air through the first bleed flowpath based on the altitude of the turbine engine.
1. A method of operating a turbine engine having a high-pressure compressor including a high-pressure compressor flowpath and a plurality of stages of high-pressure compressor rotor blades and high-pressure compressor stator vanes, and a bleed system comprising a plurality of bleed flowpaths including a first bleed flowpath from one stage of the plurality of stages and a second bleed flowpath from another stage of the plurality of stages, the method comprising:
directing compressed air through the high-pressure compressor flowpath;
directing a first portion of the compressed air through the first bleed flowpath, the first portion of the compressed air having a first mass flow;
directing a second portion of the compressed air through the second bleed flowpath, the second portion of the compressed air having a second mass flow;
determining an altitude of the turbine engine; and
changing the first mass flow of the first portion of the compressed air through the first bleed flowpath as the altitude of the turbine engine increases or decreases,
wherein a mass flow ratio of the first mass flow to the second mass flow is a first value at a first altitude, a second value at a second altitude, and a third value at a third altitude, the third altitude being greater than the second altitude, and the second altitude being greater than the first altitude.
2. The method of claim 1 , wherein the second mass flow of the second portion of the compressed air as a fraction of the compressed air through the high-pressure compressor flowpath is approximately constant as the altitude changes.
3. The method of claim 1 , wherein the first bleed flowpath and the second bleed flowpath are at successive stages of the plurality of stages.
4. The method of claim 1 , further comprising directing the first portion of the compressed air to one or more aircraft systems.
5. The method of claim 1 , further comprising directing the second portion of the compressed air to a low-pressure turbine of the turbine engine.
6. The method of claim 1 , wherein a mass flow ratio of the first mass flow to the second mass flow increases as the altitude increases.
7. The method of claim 6 , wherein the mass flow ratio of the first mass flow to the second mass flow decreases as the altitude decreases.
8. The method of claim 1 , wherein the first bleed flowpath includes a first bleed flowpath valve, and the method further comprises controlling the first bleed flowpath valve to change the first mass flow of the first portion of the compressed air through the first bleed flowpath.
9. The method of claim 1 , further comprising determining whether the altitude is increasing or decreasing.
10. The method of claim 9 , wherein changing the first mass flow includes increasing the first mass flow of the first portion of the compressed air through the first bleed flowpath as the altitude increases.
11. The method of claim 9 , wherein changing the first mass flow includes decreasing the first mass flow of the first portion of the compressed air through the first bleed flowpath as the altitude decreases.
12. The method of claim 1 , wherein the bleed system further comprises a third bleed flowpath from another stage of the plurality of stages, and the method further comprises directing a third portion of the compressed air through the third bleed flowpath.
13. The method of claim 12 , wherein the turbine engine further comprises a high-pressure turbine, and the method further comprises directing the third portion of the compressed air to the high-pressure turbine.
14. The method of claim 12 , wherein the high-pressure compressor further comprises a high-pressure compressor diffuser, the bleed system further comprises a fourth bleed flowpath from the high-pressure compressor diffuser, and the method further comprises directing a fourth portion of the compressed air through the fourth bleed flowpath.
15. The method of claim 14 , further comprising directing the fourth portion of the compressed air to one or more aircraft systems.
16. The method of claim 14 , wherein the fourth bleed flowpath includes a fourth bleed flowpath valve, and the method further comprises controlling the fourth bleed flowpath valve to open the fourth bleed flowpath valve to direct the fourth portion of the compressed air through the fourth bleed flowpath.
17. The method of claim 16 , further comprising controlling the fourth bleed flowpath valve to close to prevent the fourth portion of the compressed air from flowing through the fourth bleed flowpath.
18. The method of claim 14 , further comprising directing the fourth portion of the compressed air through the fourth bleed flowpath and preventing the first portion of the compressed air from flowing through the first bleed flowpath when the altitude is less than or equal to an altitude threshold.
19. The method of claim 18 , further comprising directing the first portion of the compressed air through the first bleed flowpath and preventing the fourth portion of the compressed air from flowing through the fourth bleed flowpath when the altitude is greater than the altitude threshold.