초록 ▼

One example of a gas turbine engine can include a first compressor and a first turbine connected to the first compressor by a first shaft. The engine can include a reheat combustor, which is disposed downstream of the first turbine, and a second turbine, which is disposed downstream of the reheat co

One example of a gas turbine engine can include a first compressor and a first turbine connected to the first compressor by a first shaft. The engine can include a reheat combustor, which is disposed downstream of the first turbine, and a second turbine, which is disposed downstream of the reheat combustor. The engine can further include a second compressor, which is connected to the second turbine by a second shaft and is disposed upstream of the first compressor. The first and second turbines can be disconnected from one another, and the first and second compressors can be disconnected from one another. The second compressor may have an outlet including a flow to the first compressor, such that the first and second turbines provide a shaft worksplit. The reheat combustor can be configured to receive fuel and generate a reheat exit temperature, so as to control an apparent capacity of the second turbine based on a plurality of parameters of the second compressor.

대표청구항 ▼

1. A gas turbine engine, comprising: a first compressor;a first turbine connected to the first compressor by a first shaft;a main combustor disposed upstream of the first turbine;a reheat combustor downstream of the first turbine;a second turbine downstream of the reheat combustor;a second compresso

1. A gas turbine engine, comprising: a first compressor;a first turbine connected to the first compressor by a first shaft;a main combustor disposed upstream of the first turbine;a reheat combustor downstream of the first turbine;a second turbine downstream of the reheat combustor;a second compressor connected to the second turbine by a second shaft and disposed upstream of the first compressor;a third turbine connected to a load; anda controller;wherein the first turbine, the second turbine, and the third turbine are disconnected from one another, and the first compressor and the second compressor are disconnected from one another, such that the first turbine and the second turbine provide a worksplit between the first shaft and the second shaft;wherein the controller is configured to: calculate an actual pressure ratio of the second compressor based on a plurality of parameters of the second compressor;calculate a corrected air flow through the second compressor based on the plurality of parameters of the second compressor;ascertain a demanded pressure ratio of the second compressor based at least in part on the calculated corrected air flow;perform a comparison of the demanded pressure ratio and the actual pressure ratio; andadjust a reheat fuel flow to the reheat combustor and a main fuel flow to the main combustor based on the comparison to adjust the actual pressure ratio toward the demanded pressure ratio, thereby controlling an apparent capacity of the second turbine, andwherein during the controlling of the apparent capacity of the second turbine by the adjusting of the reheat fuel flow to the reheat combustor and the main fuel flow to the main combustor based on the comparison, the controller decreases the main fuel flow to the main combustor and increases the reheat fuel flow to the reheat combustor in response to the comparison indicating the actual pressure ratio is less than the demanded pressure ratio, and increases the main fuel flow to the main combustor and decreases the reheat fuel flow to the reheat combustor in response to the comparison indicating the actual pressure ratio is greater than the demanded pressure ratio. 2. The gas turbine engine of claim 1, further comprising a plurality of sensors configured to detect the plurality of parameters of the second compressor, wherein the plurality of parameters of the second compressor comprises an inlet flow, an inlet temperature, an inlet pressure, a rotational speed, and an exit pressure. 3. The gas turbine engine of claim 1, wherein the first turbine is a high pressure turbine; and wherein the first compressor is a high pressure compressor disposed upstream of the main combustor. 4. The gas turbine engine of claim 1, wherein the controller is further configured to calculate an aerodynamic compressor speed of the second compressor, and wherein the demanded pressure ratio is based on the calculated corrected air flow through the second compressor and the calculated aerodynamic compressor speed. 5. The gas turbine engine of claim 2, wherein the corrected air flow through the second compressor is calculated based on the inlet flow, the inlet temperature, and the inlet pressure. 6. The gas turbine engine or claim 1, wherein the load is a third compressor connected to the third turbine by a third shaft. 7. A method of controlling a core parameter of a gas turbine engine, comprising: providing a first compressor;providing a first turbine connected to the first compressor by a first shaft;providing a main combustor disposed upstream of the first turbine;providing a reheat combustor downstream of the first turbine;providing a second turbine downstream of the reheat combustor;providing a second compressor connected to the second turbine by a second shaft and disposed upstream of the first compressor;providing a third turbine connected to a load; andproviding a controller;wherein the first turbine, the second turbine, and the third turbine are provided disconnected from one another, and the first compressor and the second compressor are provided disconnected from one another, such that the first turbine and the second turbine provide a worksplit between the first shaft and the second shaft;providing a reheat fuel flow to the reheat combustor and a main fuel flow to the main combustor;wherein the controller: detects a plurality of parameters of the second compressor;calculates an actual pressure ratio of the second compressor based on the plurality of parameters of the second compressor;calculates a corrected air flow through the second compressor based on the plurality of parameters of the second compressor;ascertains a demanded pressure ratio of the second compressor based at least in part on the calculated corrected air flow;performs a comparison of the demanded pressure ratio and the actual pressure ratio; andadjusts the reheat fuel flow to the reheat combustor and the main fuel flow to the main combustor based on the comparison to adjust the actual pressure ratio toward the demanded pressure ratio, thereby controlling an apparent capacity of the second turbine, andduring the controlling of the apparent capacity of the second turbine by the adjusting of the reheat fuel flow to the reheat combustor and the main fuel flow to the main combustor based on the comparison, the controller: decreases the main fuel flow to the main combustor and increases the reheat fuel flow to the reheat combustor in response to the comparison indicating the actual pressure ratio is less than the demanded pressure ratio, andincreases the main fuel flow to the main combustor and decreases the reheat fuel flow to the reheat combustor in response to the comparison indicating the actual pressure ratio is greater than the demanded pressure ratio. 8. The method of claim 7, wherein the actual pressure ratio is a ratio between an inlet pressure of the second compressor and an exit pressure of the second compressor. 9. The method of claim 7, wherein the plurality of parameters of the second compressor comprises an inlet flow, an inlet temperature, an inlet pressure, an exit pressure and a rotational speed. 10. The method of claim 9, further comprising calculating the corrected air flow through the second compressor based on the inlet flow, the inlet temperature, and the inlet pressure. 11. The method of claim 10, wherein the demanded pressure ratio is ascertained from a reference lookup table based on at least one of the compressor corrected air flow through the second compressor, the inlet temperature and the rotational speed. 12. The method of claim 7, wherein during the controlling of the apparent capacity of the second turbine by the adjusting of the reheat fuel flow to the reheat combustor and the main fuel flow to the main combustor based on the comparison, the controller maintains the reheat fuel flow to the reheat combustor in response to the comparison indicating the actual pressure ratio is equal to the demanded pressure ratio. 13. The method of claim 7, wherein the first turbine is a high pressure turbine and the first compressor is a high pressure compressor; andwherein the second turbine is an intermediate pressure turbine and the second compressor is an intermediate pressure compressor. 14. The method of claim 13, further comprising: wherein the third turbine is a low pressure turbine and the load is a low pressure compressor connected to the third turbine by a low shaft;wherein the first shaft, the second shaft and the low shaft are disconnected from one another. 15. A gas turbine engine, comprising: a high pressure compressor;a high pressure turbine connected to the high pressure compressor by a high pressure shaft;an intermediate pressure turbine downstream of the high pressure turbine; andan intermediate pressure compressor connected to the intermediate pressure turbine by an intermediate pressure shaft and disposed upstream of the high pressure compressor;a main combustor disposed upstream of the high pressure turbine;a reheat combustor downstream of the intermediate pressure turbine;a low pressure turbine disposed downstream of the reheat combustor,a low pressure compressor connected to the low pressure turbine by a low pressure shaft and disposed upstream of the intermediate pressure turbine; anda controller;wherein the high pressure turbine, the intermediate pressure turbine and the low pressure turbine are disconnected from one another, and the high pressure compressor, the intermediate pressure compressor and the low pressure compressor are disconnected from one another such that the intermediate pressure turbine and the low pressure turbine provide a worksplit between the low pressure shaft and the intermediate pressure shaft;wherein the controller is configured to: calculate an actual pressure ratio of the intermediate pressure compressor based on a plurality of parameters of the intermediate pressure compressor;calculate a corrected air flow through the intermediate pressure compressor based on the plurality of parameters of the intermediate pressure compressor;ascertain a demanded pressure ratio of the intermediate pressure compressor based at least in part on the calculated corrected air flow;perform a comparison of the demanded pressure ratio and the actual pressure ratio; andadjust a reheat fuel flow to the reheat combustor and a main fuel flow to the main combustor based on the comparison to adjust the actual pressure ratio toward the demanded pressure ratio, thereby controlling an apparent capacity of the intermediate pressure turbine, andwherein during the controlling of the apparent capacity of the intermediate pressure turbine by the adjusting of the reheat fuel flow to the reheat combustor and the main fuel flow to the main combustor based on the comparison, the controller decreases the main fuel flow to the main combustor and increases the reheat fuel flow to the reheat combustor in response to the comparison indicating the actual pressure ratio is less than the demanded pressure ratio, and increases the main fuel flow to the main combustor and decreases the reheat fuel flow to the reheat combustor in response to the comparison indicating the actual pressure ratio is greater than the demanded pressure ratio.