Cogen heat load matching through reheat and capacity match
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-003/10
F02C-006/00
F02C-009/54
F02C-006/18
출원번호
US-0135532
(2013-12-19)
등록번호
US-9624829
(2017-04-18)
발명자
/ 주소
Lebel, Jean-Francois
Carson, Carl
출원인 / 주소
INDUSTRIAL TURBINE COMPANY (UK) LIMITED
대리인 / 주소
Beusse Wolter Sanks & Maire
인용정보
피인용 횟수 :
0인용 특허 :
20
초록▼
One example of a gas turbine engine may include a gas generator, a reheat combustor that is disposed downstream of the gas generator, and a power turbine that is disposed downstream of the reheat combustor and includes a plurality of nozzle guide vanes. The reheat combustor is configured to increase
One example of a gas turbine engine may include a gas generator, a reheat combustor that is disposed downstream of the gas generator, and a power turbine that is disposed downstream of the reheat combustor and includes a plurality of nozzle guide vanes. The reheat combustor is configured to increase a fuel flow so as to increase a temperature of the reheat combustor and match a required exhaust temperature. The nozzle guide vanes are configured to increase a real capacity at a power turbine inlet in proportion with the required exhaust temperature. A constant apparent capacity at a gas generator exit upstream of the reheat combustor remains constant, in response to proportionately increasing the temperature and the real capacity with respect to one another.
대표청구항▼
1. A gas turbine engine, comprising: a gas generator;a reheat combustor downstream of the gas generator;a power turbine downstream of the reheat combustor and having a plurality of variable area nozzle guide vanes; anda controller configured to operate the gas turbine engine such that:the reheat com
1. A gas turbine engine, comprising: a gas generator;a reheat combustor downstream of the gas generator;a power turbine downstream of the reheat combustor and having a plurality of variable area nozzle guide vanes; anda controller configured to operate the gas turbine engine such that:the reheat combustor is configured to increase a fuel flow so as to increase a temperature of the reheat combustor and match a required exhaust temperature;the plurality of variable area nozzle guide vanes are configured to increase a real capacity at a power turbine inlet in proportion with the required exhaust temperature, wherein the real capacity is a capacity of the power turbine based on flow parameters at the power turbine inlet; anda constant apparent capacity at a gas generator exit upstream of the reheat combustor remains constant in response to proportionately increasing the temperature and the real capacity, wherein the apparent capacity is a capacity of the power turbine based on flow parameters at a gas generator exit. 2. The gas turbine engine of claim 1, wherein a position of the plurality of variable area nozzle guide vanes in turn determines a temperature of an exhaust gas when the apparent capacity remains constant. 3. The gas turbine engine of claim 1, wherein the gas generator is a two-shaft gas generator that communicates with the reheat combustor, which in turn communicates with the power turbine. 4. The gas turbine engine of claim 3, wherein the two-shaft gas generator comprises: a high pressure compressor;a high pressure turbine;a first shaft in connection between the high pressure compressor and the high pressure turbine;an intermediate pressure compressor;an intermediate pressure turbine;a second shaft in connection between the intermediate pressure compressor and the intermediate pressure turbine; andthe power turbine downstream of the intermediate pressure turbine and attached to an external load;wherein the first and second shafts are separated from one another. 5. The gas turbine engine of claim 1, wherein the gas generator is a three-shaft gas generator that communicates with the reheat combustor, which in turn communicates with the power turbine. 6. The gas turbine engine of claim 5, wherein the three-shaft gas generator comprises: a high pressure compressor;a high pressure turbine;a first shaft in connection between the high pressure compressor and the high pressure turbine;an intermediate pressure compressor;an intermediate pressure turbine;a second shaft in connection between the intermediate pressure compressor and the intermediate pressure turbine;a low pressure compressor;the power turbine attached to an external load; anda third shaft in connection between the low pressure compressor and the power turbine;wherein the first, second and third shafts are not attached to one another. 7. The gas turbine engine of claim 6, wherein the external load is one of a generator, a gas compressor and a refrigeration device. 8. The gas turbine engine of claim 1, wherein the reheat combustor has no pressure drop thereacross from the gas generator exit to the power turbine inlet. 9. The gas turbine engine of claim 1, wherein the plurality of variable area nozzle guide vanes are configured to provide a real capacity at the power turbine inlet that is within a range between an upper real capacity and a lower real capacity, that define a pair of outermost bounds for an optimal capacity associated with a heat load demanded by a cogen power station. 10. A gas turbine engine, comprising: a gas generator;a reheat combustor disposed downstream of the gas generator;a power turbine downstream of the reheat combustor having plurality of variable area nozzle guide vanes; anda controller configured to operate the gas turbine engine such that:the reheat combustor is configured to increase a fuel flow to so as to increase a temperature of the reheat combustor and match a required exhaust temperature;the plurality of variable area nozzle guide vanes are configured to match a predetermined heat load for a cogeneration plant;the plurality of variable area nozzle guide vanes are configured to be modulated and provide a plurality of real capacities at a power turbine inlet corresponding to the increased temperature of the reheat combustor, so as to match a variable heat load for the cogeneration plant and maintain a constant apparent capacity at a gas generator exit upstream of the reheat combustor,wherein the plurality of real capacities are capacities of the power turbine based on flow parameters at the power turbine inlet, andwherein the plurality of apparent capacities are capacities of the power turbine based on flow parameters at an outlet of the gas generator. 11. The gas turbine engine of claim 10, wherein a position of the plurality of variable area nozzle guide vanes in turn determines a temperature of an exhaust gas when the apparent capacity remains constant. 12. The gas turbine engine of claim 10, wherein the gas generator is one of a two-shaft gas generator and a three-shaft gas generator. 13. A method of matching a heat load demand for a cogeneration plant, the method comprising: increasing a fuel flow to a reheat combustor so as to increase a temperature of the reheat combustor and match a required exhaust temperature;increasing a real capacity at a power turbine inlet of a power turbine downstream of the reheat combustor, in proportion with the increased temperature of the reheat combustor, wherein the real capacity is a capacity of the power turbine based on flow parameters at the power turbine inlet; andmaintaining a constant apparent capacity at a gas generator exit upstream of the reheat combustor, in response to proportionately increasing the real capacity and the temperature with respect to one another, wherein the apparent capacity is a capacity of the power turbine based on flow parameters at an outlet of a gas generator,wherein increasing the real capacity and maintaining the constant apparent capacity are achieved by selecting an angle of variable area nozzle guide vanes that is appropriate to accommodate increased flow generated by the reheat combustor. 14. The method of claim 13, further comprising opening the variable area nozzle guide vanes to increase a real capacity at the power turbine inlet.
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