Compressor having low-pressure and high-pressure compressor operating at optimum ratio between pressure ratios thereof and gas turbine engine adopting the same
A compressor having a front fan, which rotates to compress intake air, a single-stage low-pressure compressor which is disposed behind the front fan to compress intake air, and a single-stage high-pressure compressor which compresses the compressed air compressed by the low-pressure compressor; a ratio (R H /R L ) of a pressure ratio (R H ) of the high-pressure compressor to a pressure ratio (R L ) of the low-pressure compressor is within a range of 4.5 to 6.0.
1. A compressor comprising:
a front fan which rotates to compress intake air;
a single-stage low-pressure compressor which is disposed behind the front fan to compress intake air; and
a single-stage high-pressure compressor which compresses the air compressed by the low-pressure compressor; wherein
a ratio (R H /R L ) of a pressure ratio (R H ) of the high-pressure compressor to a pressure ratio (R L ) of the low-pressure compressor is within a range of 4.5 to 6.0.
2. A compressor according to claim 1 , wherein the high-pressure compressor is a centrifugal type compressor, and the low-pressure compressor is an axial-flow type compressor.
3. A compressor according to claim 1 , wherein
a ratio (R F /R L ) of a pressure ratio (R F ) of the front fan to the pressure ratio (R L ) of the low-pressure compressor is within a range of 1.1 to 1.6.
4. A compressor according to claim 2 , wherein
a ratio (R F /R L ) of a pressure ratio (R F ) of the front fan to the pressure ratio (R L ) of the low-pressure compressor is within a range of 1.1 to 1.6.
5. A compressor according to claim 1 , wherein
the pressure ratio (R H ) of the high-pressure compressor is within a range of 4.0 to 10.0.
6. A compressor according to claim 2 , wherein
the pressure ratio (R H ) of the high-pressure compressor is within a range of 4.0 to 10.0.
7. A compressor according to claim 3 , wherein
the pressure ratio (R H ) of the high-pressure compressor is within a range of 4.0 to 10.0.
8. A compressor according to claim 4 , wherein
the pressure ratio (R H ) of the high-pressure compressor is within a range of 4.0 to 10.0.
9. A compressor according to claim 1 , wherein
the pressure ratio (R L ) of the low-pressure compressor is within a range of 1.1 to 2.0.
10. A compressor according to claim 2 , wherein
the pressure ratio (R L ) of the low-pressure compressor is within a range of 1.1 to 2.0.
11. A compressor according to claim 3 , wherein
the pressure ratio (R L ) of the low-pressure compressor is within a range of 1.1 to 2.0.
12. A compressor according to claim 5 , wherein
the pressure ratio (R L ) of the low-pressure compressor is within a range of 1.1 to 2.0.
13. A compressor according to claim 6 , wherein
the pressure ratio (R L ) of the low-pressure compressor is within a range of 1.1 to 2.0.
14. A compressor according to claim 7 , wherein
the pressure ratio (R L ) of the low-pressure compressor is within a range of 1.1 to 2.0.
15. A compressor according to claim 8 , wherein
the pressure ratio (R L ) of the low-pressure compressor is within a range of 1.1 to 2.0.
16. A compressor according to claim 4 , wherein
the pressure ratio (R F ) of the front fan is within a range of 1.2 to 2.5.
17. A compressor according to claim 11 , wherein
the pressure ratio (R F ) of the front fan is within a range of 1.2 to 2.5.
18. A compressor according to claim 14 , wherein
the pressure ratio (R F ) of the front fan is within a range of 1.2 to 2.5.
19. A compressor according to claim 15 , wherein
the pressure ratio (R F ) of the front fan is within a range of 1.2 to 2.5.
20. A gas turbine engine comprising:
a front fan which rotates to compress intake air;
a single-stage low-pressure compressor which is disposed behind the front fan to compress intake air;
a sing-state high-pressure compressor which compresses the air compressed by the low-pressure compressor; wherein
a ratio (R H /R L ) of a pressure ratio (R H ) of the high-pressure compressor to a pressure ratio (R L ) of the low-pressure compressor is within a range of 4.5 to 6.0;
a combustion chamber in which fuel is injected to the air compressed by the high-pressure compressor to provide combustion;
a high-pressure turbine which connects with the high-pressure compressor, and which is rotated by a combustion gas ejected from the combustion chamber;and
a low-pressure turbine which connects with the low-pressure compressor and the front fan, and which is rotated by the combustion gas ejected from the combustion chamber.