DETAILED ACTION
Notice of Pre-AIA or AIA Status
The present application, filed on or after March 16, 2013, is being examined under the first inventor to file provisions of the AIA .
This is the third office action on the merits. This office action is in response to the request for continued examination filed on 12/16/2025. Applicant has amended claims 1, 3, 10, 12, and 19 and cancelled claim 4. Claims 1, 3, 10, 12, and 19 are pending and examined.
Continued Examination Under 37 CFR 1.114
A request for continued examination under 37 CFR 1.114, including the fee set forth in 37 CFR 1.17(e), was filed in this application after final rejection. Since this application is eligible for continued examination under 37 CFR 1.114, and the fee set forth in 37 CFR 1.17(e) has been timely paid, the finality of the previous Office action has been withdrawn pursuant to 37 CFR 1.114. Applicant's submission filed on December 16, 2025 has been entered.
Priority
Applicant’s claim for the benefit of a prior-filed application under 35 U.S.C. 119(e) or under 35 U.S.C. 120, 121, 365(c), or 386(c) is acknowledged. Applicant has not complied with one or more conditions for receiving the benefit of an earlier filing date under 35 U.S.C. 120 as follows:
The later-filed application must be an application for a patent for an invention which is also disclosed in the prior application (the parent or original nonprovisional application or provisional application). The disclosure of the invention in the parent application and in the later-filed application must be sufficient to comply with the requirements of 35 U.S.C. 112(a) or the first paragraph of pre-AIA 35 U.S.C. 112, except for the best mode requirement. See Transco Products, Inc. v. Performance Contracting, Inc., 38 F.3d 551, 32 USPQ2d 1077 (Fed. Cir. 1994).
The disclosure of the prior-filed application, Application No. 17/871,270, fails to provide adequate support or enablement in the manner provided by 35 U.S.C. 112(a) or pre-AIA 35 U.S.C. 112, first paragraph for one or more claims of this application. Application 17/871,270 has no disclosure of “a recuperating heat exchanger where a first portion of a flow of the working fluid flow exhausted from the bottoming turbine section is in thermal communication with a second portion of a flow of the working fluid exhausted from the bottoming compressor section for heating the second portion of the flow of the working fluid before expansion through the bottoming turbine section” (claim 1, lines 15-19 and claim 12, lines 16-20). Accordingly, claims 1, 3, 10, 12, and 19 are not entitled to the benefit of the prior application filing date.
Claim Objections
Claims 1 and 12 are objected to because of the following informalities:
Claim 1, line 13: “to cool the working fluid flow from the bottoming turbine” is believed to be in error for --to cool the flow of the working fluid from the bottoming turbine section--
Claim 1, lines 15: “a flow of the working fluid flow” is believed to be in error for --the flow of the working fluid--
Claim 1, line 17: “a flow of the working fluid” is believed to be in error for --the flow of the working fluid--
Claim 1, lines 20-21: “the cryogenic fuel flow” is believed to be in error for --a flow of the cryogenic fuel--
Claim 1, line 22: “the working fluid flow” is believed to be in error for --the flow of the working fluid--
Claim 1, line 25: “the core engine” is believed to be in error for --the energy conversion device-- (see claim 1, line 2)
Claim 12, line 14: “the working fluid flow” is believed to be in error for --a flow of the working fluid--
Claim 12, line 18: “a flow of the working fluid” is believed to be in error for --the flow of the working fluid--
Claim 12, line 21: “the cryogenic fuel flow” is believed to be in error for --a flow of the cryogenic fuel--
Claim 12, line 23: “the combustor core engine” is believed to be in error for --the combustor of the core engine--
Appropriate correction is required.
Claim Interpretation
The following is a quotation of 35 U.S.C. 112(f):
(f) Element in Claim for a Combination. – An element in a claim for a combination may be expressed as a means or step for performing a specified function without the recital of structure, material, or acts in support thereof, and such claim shall be construed to cover the corresponding structure, material, or acts described in the specification and equivalents thereof.
The following is a quotation of pre-AIA 35 U.S.C. 112, sixth paragraph:
An element in a claim for a combination may be expressed as a means or step for performing a specified function without the recital of structure, material, or acts in support thereof, and such claim shall be construed to cover the corresponding structure, material, or acts described in the specification and equivalents thereof.
The claims in this application are given their broadest reasonable interpretation using the plain meaning of the claim language in light of the specification as it would be understood by one of ordinary skill in the art. The broadest reasonable interpretation of a claim element (also commonly referred to as a claim limitation) is limited by the description in the specification when 35 U.S.C. 112(f) or pre-AIA 35 U.S.C. 112, sixth paragraph, is invoked.
As explained in MPEP § 2181, subsection I, claim limitations that meet the following three-prong test will be interpreted under 35 U.S.C. 112(f) or pre-AIA 35 U.S.C. 112, sixth paragraph:
(A) the claim limitation uses the term “means” or “step” or a term used as a substitute for “means” that is a generic placeholder (also called a nonce term or a non-structural term having no specific structural meaning) for performing the claimed function;
(B) the term “means” or “step” or the generic placeholder is modified by functional language, typically, but not always linked by the transition word “for” (e.g., “means for”) or another linking word or phrase, such as “configured to” or “so that”; and
(C) the term “means” or “step” or the generic placeholder is not modified by sufficient structure, material, or acts for performing the claimed function.
Use of the word “means” (or “step”) in a claim with functional language creates a rebuttable presumption that the claim limitation is to be treated in accordance with 35 U.S.C. 112(f) or pre-AIA 35 U.S.C. 112, sixth paragraph. The presumption that the claim limitation is interpreted under 35 U.S.C. 112(f) or pre-AIA 35 U.S.C. 112, sixth paragraph, is rebutted when the claim limitation recites sufficient structure, material, or acts to entirely perform the recited function.
Absence of the word “means” (or “step”) in a claim creates a rebuttable presumption that the claim limitation is not to be treated in accordance with 35 U.S.C. 112(f) or pre-AIA 35 U.S.C. 112, sixth paragraph. The presumption that the claim limitation is not interpreted under 35 U.S.C. 112(f) or pre-AIA 35 U.S.C. 112, sixth paragraph, is rebutted when the claim limitation recites function without reciting sufficient structure, material or acts to entirely perform the recited function.
Claim limitations in this application that use the word “means” (or “step”) are being interpreted under 35 U.S.C. 112(f) or pre-AIA 35 U.S.C. 112, sixth paragraph, except as otherwise indicated in an Office action. Conversely, claim limitations in this application that do not use the word “means” (or “step”) are not being interpreted under 35 U.S.C. 112(f) or pre-AIA 35 U.S.C. 112, sixth paragraph, except as otherwise indicated in an Office action.
This application includes one or more claim limitations that do not use the word “means,” but are nonetheless being interpreted under 35 U.S.C. 112(f) or pre-AIA 35 U.S.C. 112, sixth paragraph, because the claim limitation(s) uses a generic placeholder that is coupled with functional language without reciting sufficient structure to perform the recited function and the generic placeholder is not preceded by a structural modifier. Such claim limitation(s) is/are: "energy conversion device" in claim 1.
Because this/these claim limitation(s) is/are being interpreted under 35 U.S.C. 112(f) or pre-AIA 35 U.S.C. 112, sixth paragraph, it/they is/are being interpreted to cover the corresponding structure described in the specification as performing the claimed function, and equivalents thereof.
A review of the specification shows that “energy conversion device” includes “a gas turbine engine” in one embodiment (¶ [0006]), and “a fuel cell” in another embodiment (¶ [0014]). Therefore, “energy conversion device” will be interpreted as “a gas turbine engine” or “a fuel cell”.
If applicant does not intend to have this/these limitation(s) interpreted under 35 U.S.C. 112(f) or pre-AIA 35 U.S.C. 112, sixth paragraph, applicant may: (1) amend the claim limitation(s) to avoid it/them being interpreted under 35 U.S.C. 112(f) or pre-AIA 35 U.S.C. 112, sixth paragraph (e.g., by reciting sufficient structure to perform the claimed function); or (2) present a sufficient showing that the claim limitation(s) recite(s) sufficient structure to perform the claimed function so as to avoid it/them being interpreted under 35 U.S.C. 112(f) or pre-AIA 35 U.S.C. 112, sixth paragraph.
Claim Rejections - 35 USC § 103
In the event the determination of the status of the application as subject to AIA 35 U.S.C. 102 and 103 (or as subject to pre-AIA 35 U.S.C. 102 and 103) is incorrect, any correction of the statutory basis (i.e., changing from AIA to pre-AIA ) for the rejection will not be considered a new ground of rejection if the prior art relied upon, and the rationale supporting the rejection, would be the same under either status.
The following is a quotation of 35 U.S.C. 103 which forms the basis for all obviousness rejections set forth in this Office action:
A patent for a claimed invention may not be obtained, notwithstanding that the claimed invention is not identically disclosed as set forth in section 102, if the differences between the claimed invention and the prior art are such that the claimed invention as a whole would have been obvious before the effective filing date of the claimed invention to a person having ordinary skill in the art to which the claimed invention pertains. Patentability shall not be negated by the manner in which the invention was made.
The factual inquiries for establishing a background for determining obviousness under 35 U.S.C. 103 are summarized as follows:
1. Determining the scope and contents of the prior art.
2. Ascertaining the differences between the prior art and the claims at issue.
3. Resolving the level of ordinary skill in the pertinent art.
4. Considering objective evidence present in the application indicating obviousness or nonobviousness.
This application currently names joint inventors. In considering patentability of the claims the examiner presumes that the subject matter of the various claims was commonly owned as of the effective filing date of the claimed invention(s) absent any evidence to the contrary. Applicant is advised of the obligation under 37 CFR 1.56 to point out the inventor and effective filing dates of each claim that was not commonly owned as of the effective filing date of the later invention in order for the examiner to consider the applicability of 35 U.S.C. 102(b)(2)(C) for any potential 35 U.S.C. 102(a)(2) prior art against the later invention.
Claims 1, 3, 10, 12, and 19 are rejected under 35 U.S.C. 103 as being unpatentable over Staubach (US 11,506,124 B2), in view of Pang (US 2014/0165572 A1) and Sen (US 2019/0249599 A1).
Regarding claim 1, Staubach teaches (Fig. 9) an aircraft propulsion system (Fig. 9 shows a turbofan) comprising:
an energy conversion device (900) that uses a cryogenic fuel (from 942 – see also col. 16, ll. 41-43: “the auxiliary cooling source 942 is a cold fuel tank (e.g., a cryogenic fuel tank)”) and air (from 912) to generate power and thermal energy (from exhaust gas flow to the right of 918);
a bottoming cycle (902) where a working fluid (supercritical CO2 – see col. 17, ll. 16-17) is circulated within a closed circuit (path of 924 → 926 → 954 → 930 → 926 → 932 → 924 is a closed loop) comprising a bottoming compressor section (930) driven by a shaft (evident by the line connecting 930 to 934 and to 924) by a bottoming turbine section (924), wherein the working fluid is compressed in the bottoming compressor section (930) and expanded through the bottoming turbine section (924) to generate shaft power (934);
a primary heat exchanger (932) providing thermal communication of thermal energy (exhaust gas flow) from the energy conversion device (900) to the working fluid (from 926) of the bottoming cycle (902);
a fuel system (940) comprising a cryogenic fuel storage tank (942 – col. 16, ll. 41-43) and a fuel flow path for routing the cryogenic fuel (path of 942 → 954 → 956 → 960 → 914) to the energy conversion device (900), wherein a fuel/working fluid heat exchanger (954) provides thermal communication between the cryogenic fuel (from 942) and a flow of the working fluid (from 926) to cool the working fluid flow from the bottoming turbine (924) to the bottoming compressor section (930);
a recuperating heat exchanger (926) where a first portion of a flow of the working fluid flow exhausted from the bottoming turbine section (924) is in thermal communication with a second portion of a flow of the working fluid (922) exhausted from the bottoming compressor section (930) for heating the second portion of the flow of the working fluid (922) before expansion through the bottoming turbine section (924);
a generator (934 – col. 16, ll. 26-27: “the power output 934 may be connected to a generator”) coupled to the shaft of the bottoming turbine section (924); and
a turbine section (916 and 918) of the energy conversion device (900).
However, Staubach does not teach a fuel/exhaust gas heat exchanger aft of the primary heat exchanger where the cryogenic fuel flow is in thermal communication with thermal energy from the energy conversion device and heated after cooling the working fluid flow exhausted from the bottoming turbine section before being communicated to the energy conversion device.
It is noted that Staubach teaches a supplemental heat exchanger (960) downstream of the primary heat exchanger (932) and before the combustor (914) of the energy conversion device (900), wherein the supplemental heat exchanger (960) “can be arranged to provide additional cooling for fluids of the engine or aircraft” (col. 16, ll. 62-64).
Pang teaches (Fig. 1) a similar system comprising:
an energy conversion device (104) that uses a fuel (“Fuel” above 112) and air (“Air” below 103) to generate power and thermal energy (shown by exhaust gas flow 154);
a bottoming cycle (106) where a working fluid (steam/water) is circulated;
a primary heat exchanger (138) providing thermal communication of thermal energy (154) from the energy conversion device (104) to the working fluid of the bottoming cycle (106); and further teaches:
an fuel/exhaust gas heat exchanger (comprising 114, 156, 158, and 160, which form a closed cycle) aft of the primary heat exchanger (138) where the fuel flow is in thermal communication with thermal energy (154) from the energy conversion device (104) – (160 is in direct thermal communication with exhaust gas flow 154) before being communicated (via combustor 105) to the energy conversion device (104).
It would have been obvious to a person having ordinary skill in the art before the effective filing date of the claimed invention to modify Staubach by including a fuel/exhaust gas heat exchange (in place of Staubach’s supplemental heat exchanger 960) downstream of the primary heat exchanger where the cryogenic fuel flow is in thermal communication with thermal energy from the energy conversion device and heated before being communicated to the energy conversion device, in order to further raise the temperature of the flow of cryogenic fuel to a level that is higher than the temperature of the cryogenic fuel flow at an outlet of the fuel/working fluid heat exchanger, thereby effectuating a rapid heating of the cryogenic fuel flow during a startup sequence of the gas turbine engine, as taught by Pang (¶ [0030], ll. 13-17 and ¶ [0031], ll. 1-3), therefore providing:
where the cryogenic fuel flow (Staubach, from 942) is in thermal communication with thermal energy (Staubach, to the right of 918) from the energy conversion device (Staubach, 900) after cooling the working fluid flow exhausted from the bottoming turbine section (Staubauch, 924) before being communicated (via Staubach’s combustor 914) to the energy conversion device (Staubach, 900).
It is noted that the above modification results in the fuel/exhaust gas heat exchanger being downstream, rather than aft, of the primary heat exchanger (the location of the fuel/exhaust gas heat exchanger is at supplemental heat exchanger 960 in Staubach’s Fig. 9, which is downstream of primary heat exchanger 932, but not “aft” of 932). It would have been obvious to a person having ordinary skill in the art before the effective filing date of the claimed invention to modify Staubach, in view of Pang, by relocating the supplemental heat exchanger 960, and thus the fuel/exhaust gas heat exchanger, to be aft of the primary heat exchanger, since it has been held that mere relocation of an element would not have modified the operation of the device (in this case, Staubach’s Fig. 9 is merely a schematic; therefore, shifting elements to be more aft in a schematic would not modify the operation of the system so long as flow lines are redrawn to maintain the same flow relationship between the elements), In re Japikse, 181 F.2d 1019, 86 USPQ 70 (CCPA 1950), MPEP 2144.04 (VI-C).
However, Staubach, in view of Pang, does not teach an electric motor coupled to an engine shaft of the core engine, wherein the electric motor is operable to receive electric power from the generator and supplement power provided by the turbine section of the energy conversion device.
It is noted that Staubach further teaches “the power output 934 may be connected to a generator (e.g., to generate electricity) or mechanically connected to a fan to drive rotation of the fan (e.g., mechanical work)” (col. 16, ll. 26-29).
Sen teaches (Fig. 3) a similar system comprising a core engine (16) and a bottoming cycle (100); and
an electric motor (132 – see ¶ [0075], ll. 11-12: “the electric machine 132 of the turbomachine 16 may be configured as an electric motor”) coupled to an engine shaft (36) of the core engine (16), wherein the electric motor (132) is operable to receive electric power from a generator (130) and supplement power provided by a turbine section (30) of the energy conversion device (16) – (¶ [0075], ll. 6-10: “when the electric machine 130 of the closed cycle heat engine 100 (configured as an electric generator) generates electrical power, the electric power may be provided to the electric machine 132 of the turbomachine 16 to add power to the turbomachine 16”).
It would have been obvious to a person having ordinary skill in the art before the effective filing date of the claimed invention to modify Staubach, in view of Pang, by including an electric motor coupled to an engine shaft of the core engine, wherein the electric motor is operable to receive electric power from the generator and supplement power provided by the turbine section of the energy conversion device, in order to allow for heat from the core engine, such as waste heat from the core engine, to be extracted, converted to useful work by the bottoming cycle, which may increase an overall efficiency of the core engine by converting waste heat to useful work, as taught by Sen (¶ [0075], ll. 13-19).
Regarding claim 3, Staubach, in view of Pang and Sen, teaches the invention as claimed and as discussed above for claim 1, and Staubach further teaches (Fig. 9) the energy conversion device (900) comprises a gas turbine engine (900 – see also col. 16, ll. 5-6) comprising a combustor (914) where the cryogenic fuel (from 942) is mixed with compressed air (from 912) and ignited to generate an exhaust gas flow, and the exhaust gas flow is routed through the primary heat exchanger (932) for heating the working fluid (from 926) of the bottoming cycle (902).
Regarding claim 10, Staubach, in view of Pang and Sen, teaches the invention as claimed and as discussed above for claim 1, and Staubach further teaches (Fig. 9) an accessory component (934, which can be a generator – see col. 16, ll. 26-27) coupled to the shaft (lines between 924, 930, and 934) driven by the bottoming turbine section (924).
Regarding claim 12, Staubach teaches (Fig. 9) a gas turbine engine (as shown in Fig. 9) comprising:
a core engine (900) comprising a combustor (914) where a cryogenic fuel (from 942 – see also col. 16, ll. 41-43: “the auxiliary cooling source 942 is a cold fuel tank (e.g., a cryogenic fuel tank)”) is mixed with compressed air (from 912) and ignited to generate an exhaust gas flow (arrow to the right of 918);
a bottoming cycle (902) where a working fluid (supercritical CO2 – see col. 17, ll. 16-17) is circulated within a closed circuit (path of 924 → 926 → 954 → 930 → 926 → 932 → 924 is a closed loop) comprising a bottoming compressor section (930) driven through a shaft (evident by the line connecting 930 to 934 and to 924) by a bottoming turbine section (924), wherein the working fluid is compressed in the bottoming compressor section (930) and expanded through the bottoming turbine section (924) to generate shaft power (934);
a primary heat exchanger (932) providing communication of thermal energy from the exhaust gas flow (from 918) to a flow of the working fluid (from 926) of the bottoming cycle (902);
a fuel system (940) comprising a cryogenic fuel storage tank (942 – col. 16, ll. 41-43) and a fuel flow path for routing the cryogenic fuel (path of 942 → 954 → 956 → 960 → 914) to the combustor (914) of the core engine (900), wherein a fuel/working fluid heat exchanger (954) provides thermal communication between the cryogenic fuel (from 942) and the working fluid (from 926) to cool the working fluid flow from the bottoming turbine section (924) to the bottoming compressor section (930);
a recuperating heat exchanger (926) where a first portion of the flow of the working fluid exhausted from the bottoming turbine section (924) is in thermal communication with a second portion of a flow of the working fluid (922) exhausted from the bottoming compressor section (930) for heating the second portion of the flow of the working fluid (922) before expansion through the bottoming turbine section (924);
a generator (934 – col. 16, ll. 26-27: “the power output 934 may be connected to a generator”) coupled to the bottoming turbine section (924) by an output shaft (line between 924 and 934); and
a turbine section (916 and 918) of the core engine (900).
However, Staubach does not teach a fuel/exhaust gas heat exchanger where the cryogenic fuel flow is heated by the exhaust gas flow after cooling the working fluid exhausted from the bottoming turbine section before being communicated to the combustor core engine.
It is noted that Staubach teaches a supplemental heat exchanger (960) for exchanging heat of the cryogenic fuel before being communicated to the combustor (914) core engine (900), wherein the supplemental heat exchanger (960) “can be arranged to provide additional cooling for fluids of the engine or aircraft” (col. 16, ll. 62-64).
Pang teaches (Fig. 1) a similar system comprising:
an energy conversion device (104) that uses a fuel (“Fuel” above 112) and air (“Air” below 103) to generate power and thermal energy (shown by exhaust gas flow 154);
a bottoming cycle (106) where a working fluid (steam/water) is circulated; and further teaches:
an fuel/exhaust gas heat exchanger (comprising 114, 156, 158, and 160, which form a closed cycle) where the fuel flow is heated by the exhaust gas flow (154) – (160 is in direct thermal communication with exhaust gas flow 154) before being communicated to the combustor (105) core engine (104).
It would have been obvious to a person having ordinary skill in the art before the effective filing date of the claimed invention to modify Staubach by including a fuel/exhaust gas heat exchange (in place of Staubach’s supplemental heat exchanger 960) where the cryogenic fuel flow is heated by the exhaust gas flow before being communicated to the combustor core engine, in order to further raise the temperature of the flow of cryogenic fuel to a level that is higher than the temperature of the cryogenic fuel flow at an outlet of the fuel/working fluid heat exchanger, thereby effectuating a rapid heating of the cryogenic fuel flow during a startup sequence of the gas turbine engine, as taught by Pang (¶ [0030], ll. 13-17 and ¶ [0031], ll. 1-3), therefore providing:
where the cryogenic fuel flow (Staubach, from 942) is heated by the exhaust gas flow (Staubach, to the right of 918) after cooling the working fluid exhausted from the bottoming turbine section (Staubauch, 924) and before being communicated to the combustor (Staubach, 914) core engine (Staubach, 900).
However, Staubach, in view of Pang, does not teach an electric motor coupled to an engine shaft of the core engine, wherein the electric motor is operable to receive electric power generated by the generator and to supplement power provided by the turbine section of the core engine.
It is noted that Staubach further teaches “the power output 934 may be connected to a generator (e.g., to generate electricity) or mechanically connected to a fan to drive rotation of the fan (e.g., mechanical work)” (col. 16, ll. 26-29).
Sen teaches (Fig. 3) a similar system comprising a core engine (16) and a bottoming cycle (100); and
an electric motor (132 – see ¶ [0075], ll. 11-12: “the electric machine 132 of the turbomachine 16 may be configured as an electric motor”) coupled to an engine shaft (36) of the core engine (16), wherein the electric motor (132) is operable to receive electric power generated by a generator (130) and to supplement power provided by a turbine section (30) of the core engine (16) – (¶ [0075], ll. 6-10: “when the electric machine 130 of the closed cycle heat engine 100 (configured as an electric generator) generates electrical power, the electric power may be provided to the electric machine 132 of the turbomachine 16 to add power to the turbomachine 16”).
It would have been obvious to a person having ordinary skill in the art before the effective filing date of the claimed invention to modify Staubach, in view of Pang, by including an electric motor coupled to an engine shaft of the core engine, wherein the electric motor is operable to receive electric power generated by the generator and to supplement power provided by the turbine section of the core engine, in order to allow for heat from the core engine, such as waste heat from the core engine, to be extracted, converted to useful work by the bottoming cycle, which may increase an overall efficiency of the core engine by converting waste heat to useful work, as taught by Sen (¶ [0075], ll. 13-19).
Regarding claim 19, Staubach, in view of Pang and Sen, teaches the invention as claimed and as discussed above for claim 12, and Staubach further teaches (Fig. 9) an accessory component (934, which can be a generator – see col. 16, ll. 26-27) coupled to be driven by the bottoming turbine section (924) through the output shaft (line between 924 and 934).
Response to Arguments
Applicant’s arguments regarding the new limitations in claims 1 and 12 have been considered but are moot in view of the new ground(s) of rejection, necessitated by Applicant's amendments. To the extent possible, Applicant's arguments have been addressed in the body of the rejections at the appropriate locations.
Applicant’s arguments against the Pang prior art have been fully considered but are not persuasive.
Regarding Applicant’s argument that “none of the elements 114, 156, 158 and 160 exposes fuel to an exhaust gas flow. Instead, a working fluid flow is used to heat the fuel flow. The exhaust gas flow heats a working fluid within an energy storage charge heat exchanger 160 (See at least paragraph 11 of Pang)”, it is evident from Pang’s Fig. 1 that the exhaust gas 154 goes through HRSG 116 to heat every element within HRSG 116. The remnants of the exhaust gas can be seen on the right-hand side of HRSG 116, which shows “Stack”. While Pang states that a working fluid within the HRSG is used to transfer energy to the thermal storage medium, the working fluid within the HRSG gets all of its thermal energy from exhaust gas 154. As evidenced by ¶ [0033], “thermal storage unit 110 can be in an off-mode where all of the exhaust energy from the gas turbine is applied to heat working fluid (e.g., water/steam) sent from HRSG 116 to steam turbine engine 118 for expansion work”. This shows that when thermal storage unit 110 is in an on-mode, some of the thermal energy from the exhaust gas flow is transferred to the thermal storage medium.
Alternatively, the loop that provides thermal energy to heat exchanger 114 may be reinterpreted as 114 → 156 → 116 → 158 → 114. In this case, the exhaust gas 154 directly heats HSRG 116, which then passes off thermal energy to element 158. This is no different from saying that the exhaust gas 154 directly heats an element (in this case, 160) within HSRG 116, which then passes off thermal energy to element 158.
Conclusion
Any inquiry concerning this communication or earlier communications from the examiner should be directed to HENRY NG whose telephone number is (571)272-2318. The examiner can normally be reached M-F 9:30 AM - 6:30 PM.
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/HENRY NG/Examiner, Art Unit 3741 /DEVON C KRAMER/Supervisory Patent Examiner, Art Unit 3741
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